WO1981001982A1 - Columnar grain ceramic thermal barrier coatings - Google Patents

Columnar grain ceramic thermal barrier coatings Download PDF

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Publication number
WO1981001982A1
WO1981001982A1 PCT/US1981/000021 US8100021W WO8101982A1 WO 1981001982 A1 WO1981001982 A1 WO 1981001982A1 US 8100021 W US8100021 W US 8100021W WO 8101982 A1 WO8101982 A1 WO 8101982A1
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WO
WIPO (PCT)
Prior art keywords
layer
mcraly
ceramic
coating
columnar
Prior art date
Application number
PCT/US1981/000021
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English (en)
French (fr)
Inventor
T Strangman
Original Assignee
United Technologies Corp
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Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=22330490&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=WO1981001982(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to BR8105750A priority Critical patent/BR8105750A/pt
Priority to DE8181900391T priority patent/DE3163778D1/de
Priority to DE198181900391T priority patent/DE42872T1/de
Publication of WO1981001982A1 publication Critical patent/WO1981001982A1/en
Priority to NO81813000A priority patent/NO156748C/no

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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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/024—Deposition of sublayers, e.g. to promote adhesion of the coating
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03C—CHEMICAL COMPOSITION OF GLASSES, GLAZES OR VITREOUS ENAMELS; SURFACE TREATMENT OF GLASS; SURFACE TREATMENT OF FIBRES OR FILAMENTS MADE FROM GLASS, MINERALS OR SLAGS; JOINING GLASS TO GLASS OR OTHER MATERIALS
    • C03C29/00—Joining metals with the aid of glass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/024—Deposition of sublayers, e.g. to promote adhesion of the coating
    • C23C14/025—Metallic sublayers
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/028—Physical treatment to alter the texture of the substrate surface, e.g. grinding, polishing
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/08—Oxides
    • C23C14/083—Oxides of refractory metals or yttrium
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S428/00—Stock material or miscellaneous articles
    • Y10S428/922—Static electricity metal bleed-off metallic stock
    • Y10S428/923—Physical dimension
    • Y10S428/924—Composite
    • Y10S428/926—Thickness of individual layer specified
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12542—More than one such component
    • Y10T428/12549—Adjacent to each other
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12583—Component contains compound of adjacent metal
    • Y10T428/1259—Oxide
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y10T428/12618—Plural oxides
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12931—Co-, Fe-, or Ni-base components, alternative to each other

Definitions

  • This invention is concerned with the field ofceramic coatings on metal substrates.
  • the coating and method described in the present application are useful for the application of protective ceramic thermal barrier coatings to gas turbine engine components. Through the use of the present coating, substantial increases in turbine operating temperatures may be possible.
  • the superalloy art has long sought to combine the properties of ceramics with the properties of metals.
  • many attempts have been made to provide protective ceramic coatings to metal articles which find application at elevated temperatures so as to combine the thermal properties of ceramics with the ductility of metals.
  • the primary problem which has not been successfully solved heretofore is that the substantial difference in the coefficient of thermal expansion of metals and ceramics invariably leads to failure of ceramic coatings under conditions of severe thermal cycling.
  • One approach which has been employed in an effort to overcome this problem is that of grading the coating from essentially all metal at the metal surface to all ceramic at the outer surface of the coating.
  • the article to be coated is held over a molten pool of material of appropriate composition which evaporates, and the vapor condenses on and coats the article.
  • This process is used in a variety of applications including the application of metallic coatings to gas turbine engine parts.
  • the application to gas turbine engine parts is described in the "Journal of Vacuum Science of Technology," Vol. 11, No. 4, July/August 1974, pgs. 641 through 646 in an article by Boone et al.
  • This article also describes the types of defects which can occur in vapor deposited coatings.
  • the most significant defect described is termed a "columnar defect" in which the coating forms as columnar grains which are poorly bonded to each other.
  • Such a structure is described as being detrimental because the exposed columnar surface greatly increased the surface exposed to the environment and because the gaps between the columns may adversely affect mechanical properties.
  • the article indicates that practical uses of vapor deposited coatings requires that the columnar type of structure be minimized.
  • Ceramic coatings have also been applied by a plasma spray process.
  • the most successful plasma spray coatings to date have been applied to articles which have been previously coated with a metallic bond coat.
  • the bond coats investigated have been the MCrAlY class of materials. In this situation, the bond coat appears to function by acting as a soft, rough layer in which the plasma spray particles are embedded forming a mechanical bond. This is described in U.S. Patent No. 4,055,705 and pending application U.S. Serial No.
  • the present invention includes a composite coating system which protects metallic articles from environmental damage especially under conditions of high temperature.
  • the novel application method also forms a part of the present invention.
  • the article to be protected is supplied with a uniform adherent MCrAlY layer. On this MCrAlY layer, there is applied a ceramic coating having a particular novel columnar microstructure.
  • the ceramic coating is comprised of many individual columnar segments which are firmly bonded to the article to be protected, but not to each other. By providing gaps between the columnar segments, the metallic substrate may expand without causing damaging stresses in the ceramic.
  • the ceramic coating is applied by a vapor deposition process.
  • a continuous alumina layer is present between the MCrAlY component and the columnar ceramic coating. This alumina layer plays a crucial role in bonding the ceramic coating to the MCrAlY layer.
  • Figure 1 is a cross sectional line drawing showing the invention coating
  • Figures 2 and 3 are a photomicrographs which show experimental coatings.
  • the thermal barrier coating system of the present invention is a composite coating which includes three interrelated elements which perform different functions.
  • the performance of the coating system is superior to that of any other known high temperature coating when evaluated in gas turbine engine environments.
  • the invention coating system provides oxidation and corrosion protection equal to that of best current coatings in combination with significant thermal barrier or insulating capabilities.
  • the major use of the invention coating is in the protection of superalloy articles.
  • Superalloys are nickel, cobalt, and iron base alloys which have exceptional properties at elevated temperatures. Typical compositions are listed in Table 1.
  • thermal barrier coating has a major use in gas turbine engines and was developed with this application in mind. However, there are many other potential applications for which this coating or some variation thereof would be well-suited.
  • the coating consists of a metallic layer of MCrAlY alloy, a continuous adherent alumina layer (formed in situ) on the metallic layer and a discontinuous pure ceramic layer of a particular columnar morphology on the alumina layer.
  • the metallic layer is comprised of a MCrAlY alloywhich has a broad composition of 10 to 30% chromium, 5 to 15% aluminum, .01 to 1% yttrium (or hafnium lanthanum, cerium and scandium) and a balance selected from the group consisting of iron, cobalt, nickel and mixtures thereof. Minor amounts of other elements may also be present.
  • MCrAlY alloy which has a broad composition of 10 to 30% chromium, 5 to 15% aluminum, .01 to 1% yttrium (or hafnium lanthanum, cerium and scandium) and a balance selected from the group consisting of iron, cobalt, nickel and mixtures thereof. Minor amounts of other elements may also be present.
  • Such alloys are known in the prior art for use alone as a protective coating and are described in various U.S. patents including 3,542,530; 3,676,085; 3,754,903 and 3,928,026 which are incorporated herein by reference.
  • This invention also contemplates the use of various interlayers between the superalloy substrate and the MCrAlY layer.
  • various interlayers between the superalloy substrate and the MCrAlY layer.
  • U.S. patent 4,005,989 it is known from U.S. patent 4,005,989 that the use of an aluminide layer (produced by aluminizing) between a substrate and a MCrAlY layer can provide improved coating durability.
  • Other materials such as platinum have also been proposed for interlayer use.
  • interlayers will be used only where necessary and only where they do not adversely affect the bond between the substrate and the MCrAlY.
  • this MCrAlY layer be applied by vapor desposition.
  • Such a deposition process in combination with peening and heat treating provides a dense adherent layer of relatively uniform thickness which is basically free from defects. A thickness of 1 - 10 mils is suitable.
  • MCrAY layer may be produced using sputtering and plasma spraying, possibly with associated post coating treatments, so long as they produce a uniform thickness high integrity coating of the desired composition.
  • the alumina layer on the MCrAlY layer is produced by oxidation of the MCrAlY layer.
  • This oxide layer is relatively thin (.01 - .1 mil), uniform and adherent. Adherence of the oxide layer is greatly improved in
  • MCrAlY alloys compared to that of similar alloys which do not contain yttrium or similar active elements. This improved adherence results from the formation of yttrium oxides which extend into the MCrAlY and are bonded to the alumina surface layer thus anchoring the surface layer and minimizing spalling.
  • the adherence of the alumina layer is essential to the adherence of the columnar ceramic layer and the presence of yttrium or equivalent oxygen active elements such as lanthanum, cerium, hafnium, and scandium or mixtures or oxide particles thereof, in the metallic coating, is important to the proper functioning of the invention coating system.
  • the final component of the thermal barrier coating is a unique columnar grained ceramic surface coating which is tightly bonded to the alumina layer.
  • the columnar grains are oriented substantially perpendicular to the surface of the substrate with free surfaces between the individual columns extending down to the aluminum oxide layer.
  • the columnar ceramic surface layer is a pure ceramic as distinguished from some prior art which has suggested the use of a graded layer incorporating substantial amounts of metal in the coatinc
  • the columnar nature of the surface layer circumvents the difference in the coefficients of thermal expansion between the substrate and the coating which is believed responsible for failure in prior art ceramic thermal barrier coatings.
  • the substrate expands at a greater rate than the ceramic surface coating and the columnar boundaries between the individual ceramic columns open to accommodate mismatch strains. This limits the stress at the interface between the substrate and the columnar ceramic to a level below thatwhich will produce a fracture of a columnar surface layer.
  • the columns have dimensions on the order of .1 mil in cross section.
  • the columnar surface layer may be any of many ceramic compositions. Most of the experimental work to date has been performed with a ceramic composed of zirconium oxide stabilized by the addition of either 20 or 35% yttria to ensure a cubic structure at all temperatures of interest. It is difficult to specify exactly the characteristics required in the ceramic material used as the columnar coating. It appears that there should be some degree of solid solubility between the columnar ceramic material and alumina. This is believed to be the major criteria which most affects the adherence of the columnar ceramic coating to the alumina layer. Other characteristics are also necessary. The columnar ceramic material should not form low melting compounds (e.g. eutectics) when in contact with alumina at elevated temperatures.
  • low melting compounds e.g. eutectics
  • the melting point (and sublimation point) of the columnar ceramic material should be substantially greater than the service temperature.
  • the columnar ceramic material should be stable in the intended environment; i.e., the material should not oxidize or otherwise react with the environment to any si ⁇ nificant extent (some ceramics such as Si 3 N 4 will oxidize at elevated temperatures but the oxidation is self limiting since the oxide produced (SiO 2 ) protects against further oxidation).
  • the columnar coating material of the present invention zirconia (preferably stabilized with a material such as yttria), alumina, ceria, mullite, zircon, silica, siliconnitride, hafnia, and certain zirconates, borides and nitrides.
  • the columnar ceramic material should have some degree of solid solubility in alumina and should be stable in the intended use envrionment. I believe that the skilled artisan will have no difficulty in selecting an appropriate ceramic based on the previous guidelines.
  • the function of the MCrAlY layer is to adhere strongly to the substrate and to produce a strong adherent continuous oxide surface layer.
  • the alumina surface layer so-produced protects the underlying MCrAlY layer and substrate against oxidation and hot corrosion and provides a firm foundation for the columnar grain ceramic surface layer.
  • the columnar grain ceramic surface layer reduces the temperature of the underlying substrate and coating layers. Because of the nature of many ceramics and the existence of the open boundaries between the columns, the ceramic surface layer is relatively transparent to oxygen and does not play a major role in reducing the oxidation of the underlying layers except to the extent that the reduction in the temperature of the underlying layers reduces the rate of oxidation. Preliminary indications are that a 5 mil thick ZrO 2 base coating can reduce substrate temperatures by from 50 to 200oF under conditions typical of those found in current gas turbine engines with cooled blades.
  • FIG. 1 shows a cross sectional line drawing of a coating according to the present invention.
  • the substrate material 1 is coated with an MCrAlY layer 2.
  • On this layer 2 there is formed an adherent alumina layer 3.
  • a columnar ceramic layer 4 adheres to the alumina layer 3.
  • Figure 2 shows a representative photomicrograph. The numbers on Figure 2 correspond to the numbers on Figure 1.
  • the initial step is the preparation of the surface to be coated.
  • the surface must be clean of all dirt, grease, oxides and the like.
  • the cleaning method I has used is vapor honing in which an aqueous abrasive slurry is propelled against the surface to be cleaned with sufficient force to remove all extraneous material from the surface. Following this step, the surface is preferably vapor degreased. While this is a satisfactory cleaning process, numerous alternative processes are possible.
  • the MCrAlY layer is applied. It is preferred that this MCrAlY layer be applied by vapor deposition.
  • the deposition process is performed by holding the surface to be coated over a pool of molten MCrAlY material in a vacuum chamber.
  • the heat source used to keep the MCrAlY molten is usually an electron beam.
  • the surface to be coated is preferably maintained at a temperature of about 1600 - 1800°F during the MCrAlY deposition process.
  • the MCrAlY layer have a thickness of about 1 to about 10 mils. MCrAlY thicknesses below about 1 mil do not provide adequate protection to the surface and thicknesses in excess of about 10 mils are prone to rippling during repeated thermal cycling.
  • the coatings are dry glass bead peened to densify any voids and to improve the coating structure. Such peening is preferred, but has not been found essential.
  • the coating is then preferably heat treated at 1975oF in hydrogen, however neither the time or temperature is particularly critical. I have used a 4-hour treatment to improve the adherence of the coating to the substrate.
  • this hydrogen heat treatment also serves to develop the desired alumina layer.
  • This oxidation occurs as a result of oxygen impurities in the hydrogen.
  • I have also employed a separate oxidation step in air in the temperature range of about 500 - 2000°F and the results appear to be similar.
  • This thermal oxidation process represents the preferred method of alumina development. It also appears possible to develop the alumina layer after the deposit of the columnar grained ceramic layer. This is especially likely in the case of zirconia based ceramics which are quite transparent to oxygen. However formation of the alumina layer prior to the columnar grained ceramic layer deposition is preferred.
  • the columnar grained ceramic surface layer is applied by a vapor deposition process.
  • the ceramic to be deposited is melted and maintained as a molten pool or evaporation source.
  • 10 - 20 mesh ceramic powder as a starting material although other starting forms are also satisfactory.
  • the substrate to be coated is positioned over the evaporation source and is manipulated to produce a uniform coating thickness and to enhance the production of a columnar structure.
  • the ceramic coating thickness may range from about 1 to about 50 mils.
  • the substrate During the ceramic coating cycle, it has been found desirable to maintain the substrate at a relatively low temperature, e.g., 1000 - 1500 F to provide a relatively coarse columnar structure and a relatively stoichiometric coating composition.
  • the coating of the invention is novel in the sense that the prior art has, in general, gone to some lengths to avoid the production of a columnar structure with inter columnar gaps which have been regarded as coating defects. This invention utilizes what has hereto fore been regarded as a coating defect to provide improved coating performance.
  • the present invention will be more readily understood by reference to the following illustrative examples.
  • the component which was coated was a first stage turbine blade from a JT9D gas turbine engine, a commercial aircraft engine of about 50,000 pounds thrust.
  • the blade was composed of alloy MAR M200 plus hafnium which has a nominal composition of 9% chromium, 10% cobalt, 12.5% tungsten, 1% columbium, 2% ticanium, 5% aluminum, 1.5% hafnium, .015% boron, .05% zirconium and .15% carbon.
  • the cast blade was cleaned by a vapor honing using an aqueous slurry of -200 mesh silica propelled at a pressure of about 60 psi against the surface of the blade. After vapor honing, the blade was vapor degreased and a 5 mil coating of NiCoCrAlY having a nominal composition of 18% chromium, 23% cobalt, 12.5% aluminum, .3% yttrium, balance nickel was deposited by electron beam vapor deposition in a vacuum chamber.
  • the blade After application of the NiCoCrAlY coating, the blade was peened using fine glass beads propelled by air pressure. This process densifies the coating. The surface roughness after peening was 35 - 40 rms. After the peening, the coated article was heat treated at 1975°F for 4 hours in hydrogen and cooled to room temperature. During this heat treatment an alumina layer formed on the MCrAlY coating.
  • the columnar ceramic was applied by vapor deposition; during coating the substrate was held at about 1,000°F.
  • the ceramic applied was cubic ZrO 2 stabilized by 20 weight percent Y 2 O 3 .
  • the starting ceramic was a 10 - 20 mesh powder.
  • the ceramic was melted by an electron beam and was maintained in a pool about 1 inch diameter.
  • the blade was held about 5 inches over the pool and was rotated over the pool at a rate of about 3 rpm for a period of about 4 hours.
  • the resultant ceramic coating was about 5 mils in thickness and each of the columns had an average cross- sectional area of about .01 sq. mil.
  • An optical micrograph of this ceramic coating structure is shown as Fig. 3.
  • the coated blades were installed in a test engine for an evaluation. The blades have accumulated approximately 100 hours of engine operating time and visual observation shows that the coating is in good condition.
  • Samples were coated and evaluated in a burner rig cycle thermal test. In this test, samples are mounted on a rotating platform and a flame formed by the combustion of jet fuel is impinged upon the samples. An instrument and control system is used to maintain the samples at a controlled temperature.
  • the samples were heated to and held at 1850°F for 4 minutes and then the flame was removed and a jet of cooling air was applied to cool the samples to below 400°F in 2 minutes. This cycle. was repeated until some sign of coating failure was observed.
  • One set of samples was prepared according to the preceding example except that no MCrAlY layer was applied, instead the vapor deposited columnar ceramic layer was applied directly to the clean superalloy substrate. The superalloy used was the same MAR M200 previously described.
  • the second set of samples was prepared using a plasma spray process to deposit a .005 inch thick layer of ZrO 2 on a .005 inch NiCoCrAlY layer which had been applied by vapor deposition. This process is consistent with the teachings of allowed U.S. application 811,807.
  • the third set of samples was prepared according to the present invention. A .005 inch thick layer of NiCoCrAlY was applied by vapor deposition and a .005 inch thick layer of ZrO 2 was subsequently applied by vapor deposition.
  • the processing sequence was identical to that described in the previous example.
  • the results of the burner rig tests using the previously described cycle were as follows. The first set of samples, those samples without the MCrAlY inter layer, failed in less than 200 cycles or 20 hours of testing.
  • the second set of samples those in which the ceramic applied by plasma spraying, failed after 1210 cycles or 121 hours of burner rig testing.
  • the third set of samples those made according to the present invention, have withstood more than 29,000 cycles or 2900 hours of testing without failure and the test is continuing.
  • the first two sets of samples failed by spallation of the ceramic from the sample. Comparison of the first sample set and third sample set clearly indicates the necessity of the MCrAlY intermediate layer if adherence of the ceramic layer is to be obtained. It appears that the provision of a MCrAlY interlayer improves the performance and adherence of the ceramic coating by a factor in excess of 100.
  • a comparison of the second and third set of samples demonstrate the significance of the particular ceramic structure and means of application of the ceramic layer. It can be seen that applying a columnar ceramic layer by vapor deposition improves the coating life by a factor of at least 20 over the life of a ceramic layer of the same composition applied by plasma spray techniques.

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PCT/US1981/000021 1980-01-07 1981-01-07 Columnar grain ceramic thermal barrier coatings WO1981001982A1 (en)

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BR8105750A BR8105750A (pt) 1980-01-07 1981-01-07 Revestimentos em colunas como barreira termica deceramica em grao
DE8181900391T DE3163778D1 (en) 1980-01-07 1981-01-07 Columnar grain ceramic thermal barrier coatings
DE198181900391T DE42872T1 (de) 1980-01-07 1981-01-07 Thermische schutzbeschichtungen aus saeulenartig koernig keramischem material.
NO81813000A NO156748C (no) 1980-01-07 1981-09-04 Superlegeringsgjenstand med et vedheftende, holdbart, keramisk og termisk barrierebelegg, samt fremgangsmaate til fremstilling av gjenstanden.

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US06/109,956 US4321311A (en) 1980-01-07 1980-01-07 Columnar grain ceramic thermal barrier coatings
US109956 1980-01-07

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2159838A (en) * 1984-06-08 1985-12-11 United Technologies Corp Surface strengthening of overlay coatings
EP0236520A1 (en) * 1984-09-10 1987-09-16 Hitachi, Ltd. Ceramic-coated, heat-resisting member and process for preparing the same
FR2651774A1 (fr) * 1989-09-08 1991-03-15 United Technologies Corp Materiau ceramique et revetement isolant a base de ce materiau.
FR2718464A1 (fr) * 1985-08-19 1995-10-13 Garrett Corp Article en super alliage ayant un revêtement de barrière thermique et sa fabrication.
US5514482A (en) * 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
EP0780484A1 (en) * 1995-12-22 1997-06-25 General Electric Company Thermal barrier coated articles and method for coating
EP2236770A3 (en) * 2009-03-30 2013-11-20 United Technologies Corporation Gas turbine engine article having columnar microstructure

Families Citing this family (167)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4457948A (en) * 1982-07-26 1984-07-03 United Technologies Corporation Quench-cracked ceramic thermal barrier coatings
DE3246504A1 (de) * 1982-12-16 1984-06-20 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Hochtemperatur-schutzschicht
US4676994A (en) * 1983-06-15 1987-06-30 The Boc Group, Inc. Adherent ceramic coatings
DE3426201A1 (de) * 1984-07-17 1986-01-23 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Verfahren zum aufbringen von schutzschichten
US4576874A (en) * 1984-10-03 1986-03-18 Westinghouse Electric Corp. Spalling and corrosion resistant ceramic coating for land and marine combustion turbines
US4889589A (en) * 1986-06-26 1989-12-26 United Technologies Corporation Gaseous removal of ceramic coatings
JP2593319B2 (ja) * 1987-10-09 1997-03-26 株式会社アサヒ電子研究所 ファイル等被検索物の個別検索装置
US4851300A (en) * 1988-05-09 1989-07-25 United Technologies Corporation Precoat for improving platinum thin film adhesion
US4916022A (en) * 1988-11-03 1990-04-10 Allied-Signal Inc. Titania doped ceramic thermal barrier coatings
US5015502A (en) * 1988-11-03 1991-05-14 Allied-Signal Inc. Ceramic thermal barrier coating with alumina interlayer
US4880614A (en) * 1988-11-03 1989-11-14 Allied-Signal Inc. Ceramic thermal barrier coating with alumina interlayer
US5601652A (en) * 1989-08-03 1997-02-11 United Technologies Corporation Apparatus for applying ceramic coatings
US5087477A (en) * 1990-02-05 1992-02-11 United Technologies Corporation Eb-pvd method for applying ceramic coatings
US5238752A (en) * 1990-05-07 1993-08-24 General Electric Company Thermal barrier coating system with intermetallic overlay bond coat
US5498484A (en) * 1990-05-07 1996-03-12 General Electric Company Thermal barrier coating system with hardenable bond coat
US5147731A (en) * 1990-08-30 1992-09-15 The United States Of America As Represented By The Secretary Of The Navy Stabilized zirconia/CoCRAlY high temperature coating
US5236745A (en) * 1991-09-13 1993-08-17 General Electric Company Method for increasing the cyclic spallation life of a thermal barrier coating
GB9204791D0 (en) * 1992-03-05 1992-04-22 Rolls Royce Plc A coated article
US5419971A (en) * 1993-03-03 1995-05-30 General Electric Company Enhanced thermal barrier coating system
AU1875595A (en) * 1994-02-16 1995-09-04 Sohl, Charles E. Coating scheme to contain molten material during gas turbine engine fires
DE69524353T2 (de) 1994-10-04 2002-08-08 General Electric Co., Schenectady Hochtemperatur-Schutzschicht
EP0786017B1 (de) * 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Schutzschicht zum schutz eines bauteils gegen korrosion, oxidation und thermische überbeanspruchung sowie verfahren zu ihrer herstellung
US5562998A (en) * 1994-11-18 1996-10-08 Alliedsignal Inc. Durable thermal barrier coating
US6103386A (en) * 1994-11-18 2000-08-15 Allied Signal Inc Thermal barrier coating with alumina bond inhibitor
GB9426257D0 (en) * 1994-12-24 1995-03-01 Rolls Royce Plc Thermal barrier coating for a superalloy article and method of application
CA2165641C (en) * 1994-12-24 2007-02-06 David Stafford Rickerby A method of applying a thermal barrier coating to a superalloy article and a thermal barrier coating
US5716720A (en) * 1995-03-21 1998-02-10 Howmet Corporation Thermal barrier coating system with intermediate phase bondcoat
US5740515A (en) * 1995-04-06 1998-04-14 Siemens Aktiengesellschaft Erosion/corrosion protective coating for high-temperature components
IN187185B (it) * 1995-04-25 2002-02-23 Siemens Ag
US5512382A (en) * 1995-05-08 1996-04-30 Alliedsignal Inc. Porous thermal barrier coating
US5683761A (en) * 1995-05-25 1997-11-04 General Electric Company Alpha alumina protective coatings for bond-coated substrates and their preparation
US5714202A (en) * 1995-06-07 1998-02-03 Lemelson; Jerome H. Synthetic diamond overlays for gas turbine engine parts having thermal barrier coatings
WO1997002947A1 (en) * 1995-07-13 1997-01-30 Advanced Materials Technologies, Inc. Method for bonding thermal barrier coatings to superalloy substrates
US5939204A (en) * 1995-08-16 1999-08-17 Siemens Aktiengesellschaft Article for transporting a hot, oxidizing gas
US6123997A (en) * 1995-12-22 2000-09-26 General Electric Company Method for forming a thermal barrier coating
US6066405A (en) * 1995-12-22 2000-05-23 General Electric Company Nickel-base superalloy having an optimized platinum-aluminide coating
US5683825A (en) 1996-01-02 1997-11-04 General Electric Company Thermal barrier coating resistant to erosion and impact by particulate matter
US5955182A (en) * 1996-02-05 1999-09-21 Kabushiki Kaisha Toshiba Heat resisting member and its production method
US5824423A (en) * 1996-02-07 1998-10-20 N.V. Interturbine Thermal barrier coating system and methods
FR2745590B1 (fr) * 1996-02-29 1998-05-15 Snecma Revetement de barriere thermique a sous-couche amelioree et pieces revetues par une telle barriere thermique
US5871805A (en) * 1996-04-08 1999-02-16 Lemelson; Jerome Computer controlled vapor deposition processes
WO1998004759A1 (en) * 1996-04-12 1998-02-05 Siemens Aktiengesellschaft Metal substrate with an oxide layer and an improved anchoring layer
US5792521A (en) * 1996-04-18 1998-08-11 General Electric Company Method for forming a multilayer thermal barrier coating
WO1997047784A1 (en) 1996-06-13 1997-12-18 Siemens Aktiengesellschaft Article with a protective coating system comprising an improved anchoring layer and its manufacture
US6306517B1 (en) 1996-07-29 2001-10-23 General Electric Company Thermal barrier coatings having an improved columnar microstructure
WO1998013531A1 (de) 1996-09-23 1998-04-02 Siemens Aktiengesellschaft Verfahren und vorrichtung zur herstellung einer wärmedämmschicht
GB2319783B (en) * 1996-11-30 2001-08-29 Chromalloy Uk Ltd A thermal barrier coating for a superalloy article and a method of application thereof
US6930066B2 (en) * 2001-12-06 2005-08-16 Siemens Westinghouse Power Corporation Highly defective oxides as sinter resistant thermal barrier coating
JP3943139B2 (ja) * 1996-12-10 2007-07-11 シーメンス アクチエンゲゼルシヤフト 高温ガスに曝される製品ならびにその製造方法
US6835465B2 (en) * 1996-12-10 2004-12-28 Siemens Westinghouse Power Corporation Thermal barrier layer and process for producing the same
US6117560A (en) * 1996-12-12 2000-09-12 United Technologies Corporation Thermal barrier coating systems and materials
US6924040B2 (en) 1996-12-12 2005-08-02 United Technologies Corporation Thermal barrier coating systems and materials
US6177200B1 (en) 1996-12-12 2001-01-23 United Technologies Corporation Thermal barrier coating systems and materials
US5891267A (en) * 1997-01-16 1999-04-06 General Electric Company Thermal barrier coating system and method therefor
US6224963B1 (en) 1997-05-14 2001-05-01 Alliedsignal Inc. Laser segmented thick thermal barrier coatings for turbine shrouds
WO1998053940A1 (de) 1997-05-28 1998-12-03 Siemens Aktiengesellschaft Metall-keramik-gradientenwerkstoff, erzeugnis daraus und verfahren zur herstellung eines metall-keramik-gradientenwerkstoffes
US6332937B1 (en) * 1997-09-25 2001-12-25 Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” Method of improving oxidation and corrosion resistance of a superalloy article, and a superalloy article obtained by the method
FR2768750B1 (fr) 1997-09-25 1999-11-05 Snecma Procede pour ameliorer la resistance a l'oxydation et a la corrosion d'une piece en superalliage et piece en superalliage obtenue par ce procede
EP1029115B1 (de) * 1997-11-03 2001-09-19 Siemens Aktiengesellschaft Erzeugnis, insbesondere bauteil einer gasturbine, mit keramischer wärmedämmschicht
GB9723762D0 (en) * 1997-11-12 1998-01-07 Rolls Royce Plc A method of coating a component
US6190124B1 (en) 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
DE19753876A1 (de) * 1997-12-05 1999-06-10 Asea Brown Boveri Eisenaluminidbeschichtung und Verfahren zum Aufbringen einer Eisenaluminidbeschichtung
US5876860A (en) * 1997-12-09 1999-03-02 N.V. Interturbine Thermal barrier coating ceramic structure
US7713297B2 (en) 1998-04-11 2010-05-11 Boston Scientific Scimed, Inc. Drug-releasing stent with ceramic-containing layer
US20040180233A1 (en) * 1998-04-29 2004-09-16 Siemens Aktiengesellschaft Product having a layer which protects against corrosion. and process for producing a layer which protects against corrosion
US6610419B1 (en) 1998-04-29 2003-08-26 Siemens Akteingesellschaft Product with an anticorrosion protective layer and a method for producing an anticorrosion protective
US5972424A (en) * 1998-05-21 1999-10-26 United Technologies Corporation Repair of gas turbine engine component coated with a thermal barrier coating
GB9811456D0 (en) 1998-05-29 1998-07-29 Rolls Royce Plc A metallic article having a thermal barrier coating and a method of application thereof
US6805750B1 (en) * 1998-06-12 2004-10-19 United Technologies Corporation Surface preparation process for deposition of ceramic coating
US6284390B1 (en) 1998-06-12 2001-09-04 United Technologies Corporation Thermal barrier coating system utilizing localized bond coat and article having the same
US6187453B1 (en) 1998-07-17 2001-02-13 United Technologies Corporation Article having a durable ceramic coating
US6007880A (en) * 1998-07-17 1999-12-28 United Technologies Corporation Method for generating a ceramic coating
US6106959A (en) * 1998-08-11 2000-08-22 Siemens Westinghouse Power Corporation Multilayer thermal barrier coating systems
US6042898A (en) * 1998-12-15 2000-03-28 United Technologies Corporation Method for applying improved durability thermal barrier coatings
US6296945B1 (en) 1999-09-10 2001-10-02 Siemens Westinghouse Power Corporation In-situ formation of multiphase electron beam physical vapor deposited barrier coatings for turbine components
US6203927B1 (en) 1999-02-05 2001-03-20 Siemens Westinghouse Power Corporation Thermal barrier coating resistant to sintering
US6060174A (en) * 1999-05-26 2000-05-09 Siemens Westinghouse Power Corporation Bond coats for turbine components and method of applying the same
US6365281B1 (en) 1999-09-24 2002-04-02 Siemens Westinghouse Power Corporation Thermal barrier coatings for turbine components
US6207297B1 (en) 1999-09-29 2001-03-27 Siemens Westinghouse Power Corporation Barrier layer for a MCrAlY basecoat superalloy combination
US20030180571A1 (en) * 1999-12-14 2003-09-25 The Penn State Research Foundation Microstructured coatings and materials
US6365236B1 (en) 1999-12-20 2002-04-02 United Technologies Corporation Method for producing ceramic coatings containing layered porosity
US6482537B1 (en) 2000-03-24 2002-11-19 Honeywell International, Inc. Lower conductivity barrier coating
US6454992B1 (en) 2000-09-29 2002-09-24 Ohio Aerospace Institute Oxidation resistant and low coefficient of thermal expansion NiA1-CoCrAly alloy
EP1199520A1 (de) 2000-10-16 2002-04-24 Siemens Aktiengesellschaft Hitzeschildstein zur Auskleidung einer Brennkammerwand, Brennkammer sowie Gasturbine
EP1251191B1 (en) 2001-04-21 2004-06-02 ALSTOM Technology Ltd A method of repairing a ceramic coating
CH695689A5 (de) * 2001-05-23 2006-07-31 Sulzer Metco Ag Verfahren zum Erzeugen eines wärmedämmenden Schichtsystems auf einem metallischen Substrat.
EP1260612A1 (en) 2001-05-25 2002-11-27 ALSTOM (Switzerland) Ltd A bond or overlay MCrAIY-coating
US6490791B1 (en) * 2001-06-22 2002-12-10 United Technologies Corporation Method for repairing cracks in a turbine blade root trailing edge
DE50202696D1 (de) 2001-08-14 2005-05-12 Alstom Technology Ltd Baden Verfahren zur Bearbeitung einer beschichteten Gasturbinenschaufel
US7204019B2 (en) 2001-08-23 2007-04-17 United Technologies Corporation Method for repairing an apertured gas turbine component
US6689487B2 (en) 2001-12-21 2004-02-10 Howmet Research Corporation Thermal barrier coating
EP1327702A1 (en) 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd Mcraiy bond coating and method of depositing said mcraiy bond coating
DE10200803A1 (de) * 2002-01-11 2003-07-31 Forschungszentrum Juelich Gmbh Herstellung eines keramischen Werkstoffes für eine Wärmedämmschicht sowie eine den Werkstoff enthaltene Wärmedämmschicht
WO2004026787A1 (de) 2002-09-14 2004-04-01 Schott Ag Verfahren zur herstellung von schichten und schichtsystemen sowie beschichtetes substrat
EP1411210A1 (en) * 2002-10-15 2004-04-21 ALSTOM Technology Ltd Method of depositing an oxidation and fatigue resistant MCrAIY-coating
EP1428982B1 (en) * 2002-12-06 2009-02-04 ALSTOM Technology Ltd A method of depositing a local MCrAIY-coating
EP1426458B1 (en) * 2002-12-06 2008-03-12 ALSTOM Technology Ltd Method of locally depositing a MCrAlY coating
US7150926B2 (en) * 2003-07-16 2006-12-19 Honeywell International, Inc. Thermal barrier coating with stabilized compliant microstructure
US20050123783A1 (en) * 2003-07-31 2005-06-09 Gregory Otto J. Composite used for thermal spray instrumentation and method for making the same
DE10342398B4 (de) * 2003-09-13 2008-05-29 Schott Ag Schutzschicht für einen Körper sowie Verfahren zur Herstellung und Verwendung von Schutzschichten
DE10342397B4 (de) 2003-09-13 2008-04-03 Schott Ag Transparente Schutzschicht für einen Körper und deren Verwendung
US20060016191A1 (en) * 2004-07-23 2006-01-26 Honeywell International Inc. Combined effusion and thick TBC cooling method
US20060057418A1 (en) * 2004-09-16 2006-03-16 Aeromet Technologies, Inc. Alluminide coatings containing silicon and yttrium for superalloys and method of forming such coatings
US9133718B2 (en) * 2004-12-13 2015-09-15 Mt Coatings, Llc Turbine engine components with non-aluminide silicon-containing and chromium-containing protective coatings and methods of forming such non-aluminide protective coatings
SG128580A1 (en) * 2005-06-08 2007-01-30 United Technologies Corp Reduced thermal conductivity thermal barrier coating by electron beam-physical vapor deposition process
US7422771B2 (en) 2005-09-01 2008-09-09 United Technologies Corporation Methods for applying a hybrid thermal barrier coating
US20090214787A1 (en) * 2005-10-18 2009-08-27 Southwest Research Institute Erosion Resistant Coatings
US7780832B2 (en) * 2005-11-30 2010-08-24 General Electric Company Methods for applying mitigation coatings, and related articles
US20070138019A1 (en) * 2005-12-21 2007-06-21 United Technologies Corporation Platinum modified NiCoCrAlY bondcoat for thermal barrier coating
CA2573585A1 (en) * 2006-02-16 2007-08-16 Sulzer Metco Coatings B.V. A component, an apparatus and a method for the manufacture of a layer system
US8123872B2 (en) * 2006-02-22 2012-02-28 General Electric Company Carburization process for stabilizing nickel-based superalloys
DE102006010860A1 (de) * 2006-03-09 2007-09-13 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer Wärmedämmschicht und Wärmedämmschicht für ein Bauteil
US20070224235A1 (en) 2006-03-24 2007-09-27 Barron Tenney Medical devices having nanoporous coatings for controlled therapeutic agent delivery
US8187620B2 (en) 2006-03-27 2012-05-29 Boston Scientific Scimed, Inc. Medical devices comprising a porous metal oxide or metal material and a polymer coating for delivering therapeutic agents
GB0610578D0 (en) 2006-05-27 2006-07-05 Rolls Royce Plc Method of removing deposits
US7740948B1 (en) 2006-05-31 2010-06-22 The United States Of America As Represented By The United States Department Of Energy Thermal barrier coatings
US8815275B2 (en) 2006-06-28 2014-08-26 Boston Scientific Scimed, Inc. Coatings for medical devices comprising a therapeutic agent and a metallic material
US8771343B2 (en) 2006-06-29 2014-07-08 Boston Scientific Scimed, Inc. Medical devices with selective titanium oxide coatings
WO2008017551A2 (de) * 2006-08-07 2008-02-14 Alstom Technology Ltd Brennkammer einer verbrennungsanlage
EP2049840B1 (de) * 2006-08-07 2018-04-11 Ansaldo Energia IP UK Limited Brennkammer einer verbrennungsanlage
CA2662808A1 (en) 2006-09-14 2008-03-20 Boston Scientific Limited Medical devices with drug-eluting coating
US7981150B2 (en) 2006-11-09 2011-07-19 Boston Scientific Scimed, Inc. Endoprosthesis with coatings
US8431149B2 (en) 2007-03-01 2013-04-30 Boston Scientific Scimed, Inc. Coated medical devices for abluminal drug delivery
US8070797B2 (en) 2007-03-01 2011-12-06 Boston Scientific Scimed, Inc. Medical device with a porous surface for delivery of a therapeutic agent
US8067054B2 (en) 2007-04-05 2011-11-29 Boston Scientific Scimed, Inc. Stents with ceramic drug reservoir layer and methods of making and using the same
US7976915B2 (en) 2007-05-23 2011-07-12 Boston Scientific Scimed, Inc. Endoprosthesis with select ceramic morphology
DE102007028109A1 (de) 2007-06-19 2008-12-24 Märkisches Werk GmbH Thermisch gespritzte, gasdichte Schutzschicht für metallische Substrate
US8002823B2 (en) 2007-07-11 2011-08-23 Boston Scientific Scimed, Inc. Endoprosthesis coating
US7942926B2 (en) * 2007-07-11 2011-05-17 Boston Scientific Scimed, Inc. Endoprosthesis coating
US9284409B2 (en) 2007-07-19 2016-03-15 Boston Scientific Scimed, Inc. Endoprosthesis having a non-fouling surface
US7931683B2 (en) 2007-07-27 2011-04-26 Boston Scientific Scimed, Inc. Articles having ceramic coated surfaces
US8815273B2 (en) 2007-07-27 2014-08-26 Boston Scientific Scimed, Inc. Drug eluting medical devices having porous layers
WO2009018340A2 (en) 2007-07-31 2009-02-05 Boston Scientific Scimed, Inc. Medical device coating by laser cladding
JP2010535541A (ja) 2007-08-03 2010-11-25 ボストン サイエンティフィック リミテッド 広い表面積を有する医療器具用のコーティング
DE102007043791A1 (de) 2007-09-13 2009-04-02 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer Wärmedämmschicht und Wärmedämmschicht
US20090118813A1 (en) * 2007-11-02 2009-05-07 Torsten Scheuermann Nano-patterned implant surfaces
US8216632B2 (en) 2007-11-02 2012-07-10 Boston Scientific Scimed, Inc. Endoprosthesis coating
US7938855B2 (en) * 2007-11-02 2011-05-10 Boston Scientific Scimed, Inc. Deformable underlayer for stent
US8029554B2 (en) 2007-11-02 2011-10-04 Boston Scientific Scimed, Inc. Stent with embedded material
US20090118818A1 (en) * 2007-11-02 2009-05-07 Boston Scientific Scimed, Inc. Endoprosthesis with coating
EP2271380B1 (en) 2008-04-22 2013-03-20 Boston Scientific Scimed, Inc. Medical devices having a coating of inorganic material
WO2009132176A2 (en) * 2008-04-24 2009-10-29 Boston Scientific Scimed, Inc. Medical devices having inorganic particle layers
EP2303350A2 (en) 2008-06-18 2011-04-06 Boston Scientific Scimed, Inc. Endoprosthesis coating
EP2307070B1 (en) * 2008-07-16 2013-03-27 Boston Scientific Scimed, Inc. Medical devices having metal coatings for controlled drug release
US8231980B2 (en) 2008-12-03 2012-07-31 Boston Scientific Scimed, Inc. Medical implants including iridium oxide
US20100154425A1 (en) * 2008-12-24 2010-06-24 United Technologies Corporation Strain tolerant thermal barrier coating system
US8071156B2 (en) 2009-03-04 2011-12-06 Boston Scientific Scimed, Inc. Endoprostheses
US8287937B2 (en) 2009-04-24 2012-10-16 Boston Scientific Scimed, Inc. Endoprosthese
US8449994B2 (en) * 2009-06-30 2013-05-28 Honeywell International Inc. Turbine engine components
US8790791B2 (en) * 2010-04-15 2014-07-29 Southwest Research Institute Oxidation resistant nanocrystalline MCrAl(Y) coatings and methods of forming such coatings
DE102010033935B4 (de) * 2010-08-10 2013-01-17 Lurgi Gmbh Brenner und Verfahren für die partielle Oxidation von flüssigem, kohlenstoffhaltigem Brennstoff
US8708659B2 (en) 2010-09-24 2014-04-29 United Technologies Corporation Turbine engine component having protective coating
US8367160B2 (en) * 2010-11-05 2013-02-05 United Technologies Corporation Coating method for reactive metal
US8460760B2 (en) 2010-11-30 2013-06-11 United Technologies Corporation Coating a perforated surface
US9511572B2 (en) 2011-05-25 2016-12-06 Southwest Research Institute Nanocrystalline interlayer coating for increasing service life of thermal barrier coating on high temperature components
US20130216798A1 (en) * 2012-02-17 2013-08-22 General Electric Company Coated article and process of coating an article
US20140050938A1 (en) * 2012-08-14 2014-02-20 General Electric Company Electrospark deposition process for oxidation resistant coating of cooling hole
US10982551B1 (en) 2012-09-14 2021-04-20 Raytheon Technologies Corporation Turbomachine blade
US9683448B2 (en) 2013-03-18 2017-06-20 Honeywell International Inc. Low conductivity thermal barrier coating
WO2015026937A1 (en) * 2013-08-22 2015-02-26 Sifco Industries, Inc. Thermal barrier systems with improved adhesion
US11479846B2 (en) 2014-01-07 2022-10-25 Honeywell International Inc. Thermal barrier coatings for turbine engine components
US9523146B1 (en) 2015-06-17 2016-12-20 Southwest Research Institute Ti—Si—C—N piston ring coatings
US10052724B2 (en) * 2016-03-02 2018-08-21 General Electric Company Braze composition, brazing process, and brazed article
US11199096B1 (en) 2017-01-17 2021-12-14 Raytheon Technologies Corporation Turbomachine blade
DE102017206063A1 (de) * 2017-04-10 2018-10-11 Siemens Aktiengesellschaft Teil- und vollstabilisiertes Zirkonoxidpulver als keramische Schicht
US11492298B2 (en) 2018-07-31 2022-11-08 General Electric Company Silicon bond coat with columnar grains and methods of its formation
EP3705597A1 (en) 2019-03-05 2020-09-09 United Technologies Corporation Thermal barrier coating with improved adhesion

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3006782A (en) * 1956-03-09 1961-10-31 Norton Co Oxide coated articles with metal undercoating
US3415631A (en) * 1965-03-12 1968-12-10 Norton Co Protective coated article
US3837894A (en) * 1972-05-22 1974-09-24 Union Carbide Corp Process for producing a corrosion resistant duplex coating
US3890456A (en) * 1973-08-06 1975-06-17 United Aircraft Corp Process of coating a gas turbine engine alloy substrate
US3976809A (en) * 1973-08-13 1976-08-24 Dowell Robert D Coating for metal surfaces and method for application
US4095003A (en) * 1976-09-09 1978-06-13 Union Carbide Corporation Duplex coating for thermal and corrosion protection
US4152223A (en) * 1977-07-13 1979-05-01 United Technologies Corporation Plasma sprayed MCrAlY coating and coating method
JPH05276314A (ja) * 1992-03-30 1993-10-22 Toshiba Corp イメージ入力装置

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3129069A (en) * 1956-10-11 1964-04-14 Gen Motors Corp Oxidation-resistant turbine blades
US2937102A (en) * 1957-03-18 1960-05-17 Zirconium Corp Of America Zirconia stabilization control
US3091548A (en) * 1959-12-15 1963-05-28 Union Carbide Corp High temperature coatings
DE1204048B (de) * 1961-03-11 1965-10-28 Heraeus Gmbh W C Verfahren zum Aufbringen von kratzfesten, transparenten oxydischen Schutzschichten auf optischen Gegenstaenden, z. B. Brillenglaesern, aus thermoplastischen Kunststoffen, insbesondere Acrylharzen, durch Vakuumaufdampfen
GB1159823A (en) * 1965-08-06 1969-07-30 Montedison Spa Protective Coatings
US3481715A (en) * 1967-02-03 1969-12-02 Ford Motor Co Sealing member for high temperature applications and a process of producing the same
US3522064A (en) * 1967-08-21 1970-07-28 Du Pont Stabilized zirconia containing niobia and calcium oxide
US3615275A (en) * 1967-12-12 1971-10-26 Texas Instruments Inc Homogeneously fine-grained vapor-deposited material in bulk form
US3754902A (en) * 1968-06-05 1973-08-28 United Aircraft Corp Nickel base superalloy resistant to oxidation erosion
US3560252A (en) * 1968-08-13 1971-02-02 Air Reduction Vapor deposition method including specified solid angle of radiant heater
US3620815A (en) * 1969-03-13 1971-11-16 United Aircraft Corp Vapor collimation in vacuum deposition of coatings
BE754553A (fr) * 1969-08-13 1971-01-18 Leybold Heraeus Verwaltung Procede et dispositif d'evaporation sous vide de corps non metalliques a point de fusion eleve
US3746571A (en) * 1971-06-29 1973-07-17 Xerox Corp Method of vacuum evaporation
US3758233A (en) * 1972-01-17 1973-09-11 Gen Motors Corp Vibration damping coatings
US3756193A (en) * 1972-05-01 1973-09-04 Battelle Memorial Institute Coating apparatus
JPS526291B2 (it) * 1972-05-11 1977-02-21
US4024294A (en) * 1973-08-29 1977-05-17 General Electric Company Protective coatings for superalloys
US3974309A (en) * 1973-12-26 1976-08-10 Ford Motor Company Method of coating a rotary internal combustion engine
US4006268A (en) * 1975-03-17 1977-02-01 Airco, Inc. Vapor collimation in vacuum deposition of coatings
JPS5276314A (en) * 1975-12-22 1977-06-27 Suwa Seikosha Kk Fusion coating pretreatment
US4109031A (en) * 1976-12-27 1978-08-22 United Technologies Corporation Stress relief of metal-ceramic gas turbine seals
US4110893A (en) * 1977-05-24 1978-09-05 United Technologies Corporation Fabrication of co-cr-al-y feed stock
US4145481A (en) * 1977-08-03 1979-03-20 Howmet Turbine Components Corporation Process for producing elevated temperature corrosion resistant metal articles
US4109061A (en) * 1977-12-08 1978-08-22 United Technologies Corporation Method for altering the composition and structure of aluminum bearing overlay alloy coatings during deposition from metallic vapor
DE2820289C2 (de) * 1978-05-10 1986-09-18 Leybold-Heraeus GmbH, 5000 Köln Verfahren zum Beschichten von metallischen Substraten mit Legierungsschichten bei erhöhter Substrattemperatur

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3006782A (en) * 1956-03-09 1961-10-31 Norton Co Oxide coated articles with metal undercoating
US3415631A (en) * 1965-03-12 1968-12-10 Norton Co Protective coated article
US3837894A (en) * 1972-05-22 1974-09-24 Union Carbide Corp Process for producing a corrosion resistant duplex coating
US3890456A (en) * 1973-08-06 1975-06-17 United Aircraft Corp Process of coating a gas turbine engine alloy substrate
US3976809A (en) * 1973-08-13 1976-08-24 Dowell Robert D Coating for metal surfaces and method for application
US4095003A (en) * 1976-09-09 1978-06-13 Union Carbide Corporation Duplex coating for thermal and corrosion protection
US4152223A (en) * 1977-07-13 1979-05-01 United Technologies Corporation Plasma sprayed MCrAlY coating and coating method
JPH05276314A (ja) * 1992-03-30 1993-10-22 Toshiba Corp イメージ入力装置

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
Battelle Pacific Northwest Laboratories Periodic Technical Report issued October 1976, BUSCH, "Develop Sputter Deposited, Graded Metal-Zr02 Coating Technology for Application to Turbine Hot Section Components". *
J. Vac Sci. Technol., Volume 11, No. 4 issued July/August 1974, BOONE et al. " Some Effects of Structure and Composition on the Properties of Electron Beam Vapor Deposited Coatings for Gas Turbine Superalloys" *
J. Vac Sci. Technol., Volume 11, No. 4 issued July/August 1974, BUNSHAH, "High-RRate Evaporation/Deposition Process of Metals, Alloys, and Ceramics for Vacuum Metallurgical Applications". *
Proceedings of 1974 Gas Turbine Materials in the Enbironment Conference issued June 1975, FAIRBANKS et al, "High-Rate Sputter Deposition of protective Coatings on Marine Gas Turbines Hot Section Superalloys". *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5514482A (en) * 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
GB2159838A (en) * 1984-06-08 1985-12-11 United Technologies Corp Surface strengthening of overlay coatings
EP0236520A1 (en) * 1984-09-10 1987-09-16 Hitachi, Ltd. Ceramic-coated, heat-resisting member and process for preparing the same
FR2718464A1 (fr) * 1985-08-19 1995-10-13 Garrett Corp Article en super alliage ayant un revêtement de barrière thermique et sa fabrication.
FR2651774A1 (fr) * 1989-09-08 1991-03-15 United Technologies Corp Materiau ceramique et revetement isolant a base de ce materiau.
EP0780484A1 (en) * 1995-12-22 1997-06-25 General Electric Company Thermal barrier coated articles and method for coating
EP2236770A3 (en) * 2009-03-30 2013-11-20 United Technologies Corporation Gas turbine engine article having columnar microstructure

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AU6774381A (en) 1981-08-07
BR8105750A (pt) 1981-11-24
KR840001683B1 (ko) 1984-10-15
IT1134957B (it) 1986-08-20
JPS57500291A (it) 1982-02-18
EP0042872A1 (en) 1982-01-06
NO813000L (no) 1981-09-04
US4321311A (en) 1982-03-23
IT8119030A0 (it) 1981-01-07
EP0042872A4 (en) 1982-06-10
DE3163778D1 (en) 1984-07-05
BE886975A (fr) 1981-05-04
KR830005068A (ko) 1983-07-23
JPH0118993B2 (it) 1989-04-10
AU543223B2 (en) 1985-04-04
NO156748B (no) 1987-08-10
DE42872T1 (de) 1983-01-20
EP0042872B1 (en) 1984-05-30
NO156748C (no) 1987-11-18
CA1167329A (en) 1984-05-15
IL61878A (en) 1984-09-30

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