EP0532252A1 - Composant en super-alliage pourvu d'un revêtement protecteur contenant des dispersions et procédé de sa fabrication - Google Patents

Composant en super-alliage pourvu d'un revêtement protecteur contenant des dispersions et procédé de sa fabrication Download PDF

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Publication number
EP0532252A1
EP0532252A1 EP92308099A EP92308099A EP0532252A1 EP 0532252 A1 EP0532252 A1 EP 0532252A1 EP 92308099 A EP92308099 A EP 92308099A EP 92308099 A EP92308099 A EP 92308099A EP 0532252 A1 EP0532252 A1 EP 0532252A1
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EP
European Patent Office
Prior art keywords
coating
superalloy
yttrium
nickel
percent
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP92308099A
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German (de)
English (en)
Inventor
Edward Harvey Goldman
David John Wortman
Ramgopal Darolia
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP0532252A1 publication Critical patent/EP0532252A1/fr
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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
    • C23C4/04—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
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • 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

  • This invention relates to the protection of superalloys to be used at elevated temperatures, and, more particularly, to superalloy articles protected by coatings.
  • nickel-base superalloys which are alloys of nickel with additions of a number of other elements such as, for example, chromium, cobalt, aluminum, and tantalum.
  • the compositions of these superalloys are carefully engineered to maintain their strength and other mechanical properties even during use at the high temperature of engine operation, which is in the neighborhood of 2000°F or more.
  • the materials used in the jet engines must operate at high temperatures, but additionally are subjected to oxidative and corrosive conditions. Oxidation of materials such as nickel and many of its alloys is rapid at engine operating temperatures. The engine components are also subjected to corrosive attack by chemicals in the burned fuel, as well as ingested agents such as salt that might be drawn into the engine as it operates near an ocean. The materials that have the best mechanical properties at high temperatures often are not as resistant to oxidation and corrosion as other materials, and there is an ongoing search for materials that offer a compromise between the best mechanical properties and the best oxidation and corrosion resistance.
  • High operating temperatures can also be achieved by other techniques not related directly to the alloy compositions used in the components. For example, control of grain structures and use of single crystals can result in improved properties. Cooling passages may be provided in the components, and cooling air passed through them to lower their actual operating temperature.
  • a thin protective metallic coating is deposited upon the component.
  • the coating protects the substrate from oxidation and corrosion damage.
  • the coating must be adherent to the superalloy substrate and must remain adherent through many cycles of heating to the operating temperature and then cooling back to a lower temperature when the engine is idling or turned off. Because materials of different compositions have different coefficients of thermal expansion, differential strains develop between the coating and the component.
  • the thin coatings have been made of materials that are relatively weak and ductile. Such a coating can plastically deform either in tension or compression to remain adherent to the surface of the substrate as the substrate is heated and cooled.
  • Most coatings for nickel-base superalloys have been made of alloys of nickel, chromium, aluminum, and yttrium, which are termed NiCrAlY alloys, and nickel, cobalt, chromium, aluminum, and yttrium, which are termed NiCoCrAlY alloys.
  • MCrAlX where M represents nickel, cobalt, iron or some combination thereof and X represents yttrium, hafnium, tantalum, silicon or some combination thereof, is a widely used generic description for this type of alloy. While such alloys:contain many of the same elements as the substrate materials, the proportions of those elements have been adjusted to enhance oxidation and corrosion resistance rather than mechanical properties. They therefore lack the strength to serve as the structural components themselves, but serve well as protective coatings.
  • the present invention fulfills this need, and further provides related advantages.
  • the present invention provides a class, and specific alloy compositions, of metallic coating materials useful in protecting high-temperature superalloys.
  • the compositions are compositionally and structurally compatible with the superalloy substrates, protect against oxidation and corrosion damage, and remain adherent, crack-free, and protective for greater periods of time than prior metallic superalloy coatings.
  • the coatings are formulated and applied by conventional techniques.
  • a coated superalloy component comprises a substrate article formed of a superalloy and an adherent coating over the substrate.
  • the coating is a nickel-base superalloy additionally containing at least about 0.3 volume percent of dispersed particles of an oxide of yttrium, hafnium, a rare earth, or combinations thereof.
  • the coatings of the invention represent a significant departure from conventional thinking in the metallic coating area.
  • metallic superalloy coatings were made weak and ductile, to accommodate the strains imposed by the substrate as the component was repeatedly heated and cooled.
  • the coating is deformed in complex planar strain conditions that are dictated by the deformation of the more massive substrate.
  • the coating must deform plastically and/or in creep to a new set point during the temperature and load cycling of the engine, and a weak coating was deemed most desirable to operate under these constraints.
  • the present invention therefore provides an oxide-dispersion containing coating, a coated article, and a method for preparation thereof.
  • the oxide-containing coating is more resistant to thermal fatigue damage than the NiCrAlY or NiCoCrAlY alloys conventionally used as metallic coating materials, without sacrificing oxidation and corrosion resistance.
  • the present invention provides an important advance in the art of superalloys, as well as a departure from the conventional thought in the field.
  • the coating of the invention permits a controllable improvement to the properties of the coating through selection of the fraction of dispersoid, while retaining the chemical components that lead to oxidation and corrosion resistance.
  • the coating of the invention is preferably used with nickel-base superalloys, in applications such as a jet engine gas turbine blade 10 illustrated in Figure 1, or a gas turbine vane which has a similar appearance in relevant respects.
  • the blade 10 may be formed of any suitable superalloy such as Rene′ 80, a well known nickel-base superalloy which has a nominal composition, in weight percent, of 14 percent chromium, 9.5 percent cobalt, 5 percent titanium, 4 percent tungsten, 4 percent molybdenum, 3 percent aluminum, 0.17 percent carbon, 0.06 percent zirconium, 0.015 percent boron, and the balance nickel.
  • Rene′ N4 Another example is a more advanced nickel-base superalloy such as Rene′ N4, having a composition, in weight percent, of 7.5 cobalt, 9.0 chromium, 3.7 aluminum, 4.2 titanium, 1.5 percent molybdenum, 4.0 percent tantalum, 6.0 percent tungsten, 0.5 percent niobium, and balance nickel.
  • substrate superalloys are presented as examples, and the coatings are not limited for use with these substrates.
  • Such a blade 10 includes an airfoil section 12 against which hot combustion gases are directed when the engine operates, and whose surface is subjected to severe oxidation and corrosion attack during service. If the surface of the airfoil section 12 is not protected against oxidation and corrosion in some fashion, it will normally last at most only a few cycles of operation.
  • the airfoil section 12 is anchored to a turbine disk (not shown) through a root section 14.
  • cooling passages 16 are present in the airfoil section 12, through which cool bleed air is forced to remove heat from the blade 10.
  • the blade 10 is normally prepared by a casting and solidification procedure well known to those skilled in the art, such as investment casting or, more preferably, directional solidification or single crystal growth.
  • the airfoil section 12 is protected by a metallic protective coating 20, as illustrated in detail in Figure 2, which depicts an enlargement of a section through the surface portion of the blade 10.
  • the nickel-base superalloy of the blade 10 (or of a gas turbine vane or other superalloy component) forms a substrate 22 upon which and over which the coating 20 is deposited.
  • the coating 20 contains at least about 0.3 percent by volume of a dispersion of oxide particles 24 formed by the oxidation of yttrium and/or rare earth elements. These particles are typically equiaxed or roughly spherical in shape, but they could have an elongated shape. (In Figure 2, both the volume fraction of the dispersoid and its size are exaggerated for purposes of clarity of illustration.)
  • the coating may be applied by vacuum or air plasma spraying a layer of the coating composition onto the surface of the component.
  • vacuum and air plasma spraying are known to those skilled in the art.
  • powders having a desired net composition are melted (at least partially) in a plasma and propelled against the substrate, where they solidify to form the coating.
  • the powders are desirably uniform in composition, but plasma spray coating can also be accomplished using particles of different compositions having a net desired composition, which intermix while molten.
  • the operation is carried out in a vacuum, or in inert gas at a pressure lower than about 0.1 atmosphere.
  • the thickness of the coating is typically from about 0.001 to about 0.010 inch, most preferably about 0.004 inch.
  • a method for preparing a coated superalloy component comprises the steps of providing a substrate article formed of a nickel-base superalloy; and applying an adherent coating to the article by a thermal spray process, the coating being a nickel-base superalloy additionally containing at least about 0.3 volume percent of dispersed oxide particles formed of an element selected from the group consisting of yttrium, hafnium and the rare earths.
  • the superalloy of the coating can be any coating designed for protection of the substrate against oxidation and corrosion.
  • the oxides can be simple oxides or complex oxides containing one or more of the elements yttrium, hafnium and the rare earths. In this method, the oxide dispersoids are present in the plasma-sprayed powders during the spraying process.
  • a method for preparing a coated superalloy component comprises the steps of providing a substrate article formed of a nickel-base superalloy; and applying an adherent coating to the article by a thermal spray process such as vacuum or air plasma spray, the coating being a nickel-base superalloy additionally containing a sufficient amount of an element selected from the group consisting of yttrium, hafnium, and the rare earths, and combinations thereof, to form at least about 0.3 volume percent of dispersed oxide particles upon subsequent oxidation heat treatment.
  • a metallic alloy is applied to the surface.
  • the superalloy of the coating can be any coating designed for protection of the substrate against oxidation and/or corrosion, but additionally has a sufficient excess amount of yttrium, hafnium or a rare earth to form the oxide dispersoids during a subsequent heat treatment. After the coating is applied, the coated component is heat treated in an oxidizing atmosphere to form the oxide dispersoids within the superalloy matrix.
  • the oxides can be simple oxides or complex oxides containing one or more of the elements yttrium, hafnium and the rare earths.
  • the coating must contain at least about 0.3 volume percent of the oxide dispersoids, or the individual dispersoid particles will be too widely spaced to have a significant effect on reduction of cracking of the coating during thermal fatigue cycling. Larger amounts are acceptable, as long as they do not lead to brittleness of the coating. From about 0.5 to about 1.0 volume percent of the dispersoids is preferred.
  • the term "the rare earths” comprehends those elements of the lanthanide series of the periodic table, atomic numbers 57-71 inclusive. These elements include lanthanum, cerium, praseodymium, neodymium, prometheum, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, and lutetium. Although yttrium, atomic number 39, and hafnium, atomic number 72, are sometimes grouped together with the rare earths, they are separately identified herein, and not included among the rare earths.
  • a conventional NiCoCrAlY coating material was modified by adding 0.5 volume percent yttrium oxide and also alloying elements to strengthen the grain boundary regions of the coating.
  • a standard NiCoCrAlY coating alloy has a composition, in weight percent, of about 20-23 percent cobalt, 18 percent chromium, 12.5 percent aluminum, 0.3 percent yttrium, and balance nickel.
  • a satisfactory coating alloy is obtained by leaving the major alloying elements substantially as they are, and adding carbon, boron, or zirconium to strengthen the grain boundaries of the coating, and sufficient yttrium oxide to produce a dispersion of about 0.5 volume percent yttrium oxide (Y2O3) particles throughout the coating.
  • the grain boundary strengthener is preferably up to about 0.07 weight percent carbon, up to about 0.030 weight percent zirconium, and up to about 0.030 percent boron, or combinations thereof.
  • the preferred minimum contents are about 0.01 percent carbon, about 0.005 percent zirconium, and about 0.005 percent boron. Amounts below those indicated do not strengthen the grain boundaries to any appreciable degree, which may lead to premature failure of the coating due to grain boundary creep. Amounts above the maximums can lead to grain boundary embrittlement, also a cause of premature failure.
  • a powder is formed from material of this composition by any convenient known method, such as mechanical alloying, and then applied to the component substrate by vacuum plasma spraying.
  • a coated superalloy component comprises a substrate article formed of a superalloy; and an adherent coating over the substrate, the coating being a nickel-base superalloy containing at least one gamma phase grain boundary strengthener selected from the group consisting of up to about 0.07 percent carbon, up to about 0.030 percent zirconium, and up to about 0.030 percent boron, and additionally containing at least about 0.3 volume percent of dispersed oxide particles formed of an element selected from the group consisting of yttrium, hafnium, the rare earths, and combinations thereof.
  • the presently most preferred coating according to the invention has a metallic matrix composition, in weight percent, of 20 percent cobalt, 18 percent chromium, 12 percent aluminum, 0.05 percent carbon, 0.015 percent boron, 0.015 percent zirconium, 0.3 percent yttrium (present in the metallic form), and 1.0 percent silicon.
  • About 0.5 percent by volume of yttrium oxide particulate material was mixed with the metallic matrix composition by mechanical alloying. (Yttrium is present in this coating as a metallic alloying element, below its solubility limit, and also as the oxide dispersoid yttrium oxide.)
  • This coating may be applied by any type of plasma spraying, but preferably by vacuum plasma spraying, which was employed in the examples described herein.
  • the coating of the preceding paragraph was applied to a simulated gas turbine blade made of the Rene′ N4 superalloy discussed previously. These simulated blades were comparatively tested against identical simulated blades of the same Rene′ N4 superalloy, except having a CODEP coating prepared by the pack-diffusion process disclosed in U.S. Patent No. 3,540,878. In a burner rig thermal fatigue test, the coated blades were cycled between 970°F and 1800°F for 5000 cycles, and inspected. The blades coated with the dispersion-containing coating exhibited approximately the same number of cracks as for the CODEP coated blades, but the severity of the cracks was much less for the dispersion-containing coatings.
  • a set of test specimens with the dispersion-containing coating had an average lifetime of 585 hours, as compared with 125 hours for identical CODEP-coated specimenso
  • the dispersion-containing coating had an average life of at least 1600 hours (at which time the test was discontinued), compared to only 550 hours for the CODEP-coated blade.
  • the dispersion-containing coating of the invention produces improved results in simulated operating environments as compared with state-of-the-art CODEP coatings.
  • Coatings of the present invention are typically stronger than conventional NiCoCrAlY coatings.
  • the rupture life of a conventional NiCoCrAlY coating, tested at 1600°F and 3,000 pounds per square inch stress is about 13 hours.
  • the coating described above has a rupture life under the same test conditions of about 23 hours. After heat treating the coating 2 hours at 2310°F, the rupture life was increased to 506 hours. The increased strength is believed to contribute to the observed reduction in severity of cracks in the coating.
  • the present approach provides an advancement in the protection of superalloy substrates, and more particularly nickel-base superalloy substrates by metallic protective coatings.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP92308099A 1991-09-09 1992-09-08 Composant en super-alliage pourvu d'un revêtement protecteur contenant des dispersions et procédé de sa fabrication Withdrawn EP0532252A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US75694791A 1991-09-09 1991-09-09
US756947 1991-09-09

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EP0532252A1 true EP0532252A1 (fr) 1993-03-17

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EP (1) EP0532252A1 (fr)
JP (1) JPH05195186A (fr)
CA (1) CA2076091A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0652299A1 (fr) * 1993-11-08 1995-05-10 ROLLS-ROYCE plc Composition de revêtement résistant à la corrosion et l'oxydation
US5897947A (en) * 1995-01-31 1999-04-27 Maschinenfabrik Rieter Ag Method of coating and thread guiding elements produced thereby
EP0933448A1 (fr) * 1998-02-02 1999-08-04 General Electric Company Revêtement de liaison amélioré d'aluminure par diffusion pour systèmes à couche barrière thermique et son procédé de fabrication
EP1036850A1 (fr) * 1998-06-15 2000-09-20 Mitsubishi Heavy Industries, Ltd. ALLIAGE MONOCRISTALLIN A BASE DE Ni DOTE D'UN FILM DE REVETEMENT PERMETTANT D'EMPECHER LA CASSURE DE RECRISTALLISATION
EP2508644A1 (fr) * 2011-04-07 2012-10-10 General Electric Company Procédés de formation d'un revêtement résistant à la dispersion d'oxyde
CN113891953A (zh) * 2019-05-27 2022-01-04 赛峰集团 防腐蚀的方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7341758B2 (en) * 2003-04-24 2008-03-11 General Electric Company Method for preparing and ultrasonically testing a thermal-spray coated article

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2367833A1 (fr) * 1976-10-15 1978-05-12 Bbc Brown Boveri & Cie Couche anticorrosive pour alliages resistant a la chaleur
US4230748A (en) * 1979-08-15 1980-10-28 Eutectic Corporation Flame spray powder mix
GB2095700A (en) * 1981-03-31 1982-10-06 Howmet Turbine Components Superalloy coating compositions
EP0157231A1 (fr) * 1984-04-05 1985-10-09 The Perkin-Elmer Corporation Poudre pour pulvérisation thermique recouverte d'aluminium et d'oxyde d'yttrium
WO1987006273A2 (fr) * 1986-04-10 1987-10-22 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Couche protectrice contre l'usure et la corrosion par frottement, en particulier de pieces mecaniques metalliques accouplees par liaison de force

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2367833A1 (fr) * 1976-10-15 1978-05-12 Bbc Brown Boveri & Cie Couche anticorrosive pour alliages resistant a la chaleur
US4230748A (en) * 1979-08-15 1980-10-28 Eutectic Corporation Flame spray powder mix
GB2095700A (en) * 1981-03-31 1982-10-06 Howmet Turbine Components Superalloy coating compositions
EP0157231A1 (fr) * 1984-04-05 1985-10-09 The Perkin-Elmer Corporation Poudre pour pulvérisation thermique recouverte d'aluminium et d'oxyde d'yttrium
WO1987006273A2 (fr) * 1986-04-10 1987-10-22 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Couche protectrice contre l'usure et la corrosion par frottement, en particulier de pieces mecaniques metalliques accouplees par liaison de force

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
THIN SOLID FILMS vol. 173, no. 1, 1 June 1989, LAUSANNE,CH pages 99 - 107 B. GUDMUNDSSON 'yttrium oxides in vacuum-plasma-sprayed CoNiCrAlY coatings' *

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0652299A1 (fr) * 1993-11-08 1995-05-10 ROLLS-ROYCE plc Composition de revêtement résistant à la corrosion et l'oxydation
US5897947A (en) * 1995-01-31 1999-04-27 Maschinenfabrik Rieter Ag Method of coating and thread guiding elements produced thereby
EP0933448A1 (fr) * 1998-02-02 1999-08-04 General Electric Company Revêtement de liaison amélioré d'aluminure par diffusion pour systèmes à couche barrière thermique et son procédé de fabrication
US6168874B1 (en) 1998-02-02 2001-01-02 General Electric Company Diffusion aluminide bond coat for a thermal barrier coating system and method therefor
US6440496B1 (en) 1998-02-02 2002-08-27 General Electric Company Method of forming a diffusion aluminide coating
EP1036850A1 (fr) * 1998-06-15 2000-09-20 Mitsubishi Heavy Industries, Ltd. ALLIAGE MONOCRISTALLIN A BASE DE Ni DOTE D'UN FILM DE REVETEMENT PERMETTANT D'EMPECHER LA CASSURE DE RECRISTALLISATION
EP1036850A4 (fr) * 1998-06-15 2003-05-02 Mitsubishi Heavy Ind Ltd ALLIAGE MONOCRISTALLIN A BASE DE Ni DOTE D'UN FILM DE REVETEMENT PERMETTANT D'EMPECHER LA CASSURE DE RECRISTALLISATION
EP2508644A1 (fr) * 2011-04-07 2012-10-10 General Electric Company Procédés de formation d'un revêtement résistant à la dispersion d'oxyde
US8313810B2 (en) 2011-04-07 2012-11-20 General Electric Company Methods for forming an oxide-dispersion strengthened coating
CN113891953A (zh) * 2019-05-27 2022-01-04 赛峰集团 防腐蚀的方法
CN113891953B (zh) * 2019-05-27 2023-09-26 赛峰集团 防腐蚀的方法

Also Published As

Publication number Publication date
CA2076091A1 (fr) 1993-03-10
JPH05195186A (ja) 1993-08-03

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