US3874901A - Coating system for superalloys - Google Patents

Coating system for superalloys Download PDF

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Publication number
US3874901A
US3874901A US353660A US35366073A US3874901A US 3874901 A US3874901 A US 3874901A US 353660 A US353660 A US 353660A US 35366073 A US35366073 A US 35366073A US 3874901 A US3874901 A US 3874901A
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aluminum
coating
percent
nickel
cobalt
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Expired - Lifetime
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US353660A
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English (en)
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Iii John R Rairden
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General Electric Co
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General Electric Co
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Application filed by General Electric Co filed Critical General Electric Co
Priority to US353660A priority Critical patent/US3874901A/en
Priority to NL7400370A priority patent/NL7400370A/xx
Priority to GB131874A priority patent/GB1457033A/en
Priority to JP49019604A priority patent/JPS501932A/ja
Priority to IT21254/74A priority patent/IT1009812B/it
Priority to FR7413685A priority patent/FR2226484B1/fr
Priority to DE2418879A priority patent/DE2418879A1/de
Priority to BE143494A priority patent/BE814053A/fr
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Publication of US3874901A publication Critical patent/US3874901A/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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/58—After-treatment
    • C23C14/5806—Thermal treatment
    • 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
    • C23C14/14—Metallic material, boron or silicon
    • C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
    • 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
    • C23C14/58—After-treatment
    • 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
    • C23C14/58—After-treatment
    • C23C14/5893—Mixing of deposited 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
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00

Definitions

  • ABSTRACT A protective Coating system is provided for nickelbase and cobalt-base superalloys which is capable of imparting oxidation and corrosion resistance at elevated temperatures.
  • the superalloy body is first coated by physical vapor deposition with composition consisting essentially of chromium, aluminum and, optionally.
  • the body is coated with an overlayer of aluminum by physical vapor deposition and heat treated to cause the interdiffusion of aluminum into the first coating layer and thereby greatly enhance the hot corrosion and oxidation resistance of the coating system.
  • the superalloys are heat-resistant materials having superior strengths at high temperatures. Many of these alloys contain iron. nickel or cobalt alone or in combination as the principal alloying elements together with chromium to impart surface stability and usually contain one or more minor constituents. such as molybde num. tungsten. columbium. titanium and aluminum for the purpose of effecting strengthening. The physical properties of the superalloys make them particularly useful in the manufacture of gas turbine engine components.
  • coating compositions consisting essentially of chromium. aluminum and. optionally. a member selected from the group consisting of yttrium and the rare earth elements and a metal selected from the group consisting of iron. cobalt and nickel.
  • Illustrative coatings wherein the compositions are given in weight percent are designated as follows:
  • the application of the coating composition to a variety of substrates. such as nickel-base and cobalt-base superalloys may be achieved by physical vapor deposition in a vacuum chamber. During this procedure. the composition is thermally evaporated from a source heated. for example. by an electron beam. and a thin metal coating is condensed on the surface of the workpiece. Layers of the coating are formed as the workpiece is rotated until the thickness is. preferably. in the range of about I-7 mils. Unfortunately. the deposited coating has radially oriented defects which are the sites of attack by oxidizing and/or corrosive atmospheres at high temperatures. Such defects can lead to premature failure of the coating.
  • the effectiveness of the coating system may be explained by the fact that the first coating layer exhibits flaws or boundaries that are oriented in a perpendicular direction to the deposition plane. Upon exposure to a corrosive environment. these flaws or boundaries are preferentially attacked resulting in premature failure of the coating. The application of an aluminum overcoat that is subsequently suitably heat treated prevents this type of failure and thereby substantially increases the life of the coated article.
  • the concentration profile of our novel coating system indicates the presence of a high concentration of aluminum on the outer surface of the coating which may also contribute to the improved properties.
  • the coated superalloy bodies prepared by our invention are particularly useful in making gas turbine engine components.
  • FIG. I is a photomicrograph (500X of a Udimet 500 nickel-base superalloy body coated with a CoCrAIY coating.
  • FIG. 2 is a photomicrograph (500X) of a Udimet 500 nickel-base superalloy body coated with a first CoCr- AIY coating.and then an aluminum layer and heat treated for three hours at 1 I C. in argon to form a composite coating according to the method of our invention.
  • FIG. 3 is a photomicrograph (500X) illustrating the effect of corrosion on a CoCrAIY coated superalloy body.
  • FIG. 4 is a photomicrograph (500X) illustrating the effect of corrosion on a coated superalloy body coated as shown in FIG. 2.
  • the superalloys are strong. high temperature materials which are particularly useful in gas turbine engines. A substantial listing of these materials is set forth by W. F. Simmons. ('onipilatiun qfC/zenzicul (rmiposirirmx and Rupture Strengths of Supera/loyv. ASTM Data Series Publication No.'DS9E. and may be represented by the nominal compositions in weight percent of the following superalloys:
  • the first coating of our protective coating system is designated herein as MCrAlY" or MCrAl' coating wherein M is a member selected from the group consisting of iron. cobalt. and nickel.
  • This coating is broadly defined as consisting essentially in weight percent of the following nominal compositions:
  • Ingredients Weight '2 ('hromium 1-1 35 Aluminum 4J0 Yttrium d Iron t (obalt 1 Balance Nickel Included in this formulation are the compositions designated hereinabove as FeCrAlY. CoCrAIY. and NiCr- AIY and also includes these compositions in which yttrium is entirely absent.
  • the MCrAlY or MCrAl coating is applied to the substrate by a physical vapor deposition technique which is described in considerable detail in I'upur [)U/mXi/IHII. Edited by C. F. Powell et al.. John Wiley &; Sons. New York (196(1). Accordingly. the coating is evaporated and deposited in a vacuum chamber. 'lypically.
  • the metal alloy is heated by an electron beam focused on the metal alloy ingot to evaporate the metal to a vapor.
  • the vapor condenses as a coating. preferably about l-7 mils in thickness on the workpiece being coated.
  • the material to be applied is heated in a high vacuum to a temperature at which its vapor pressure is about It) torr or greater whereupon it emits molecular rays in all directions.
  • the vacuum must be very high to permit the molecular rays to travel from their source without disturbance until they hit the surface of the object to be coated.
  • a photomicrograph of a nickel-base superalloy coated with a (oCrAlY coating is shown in FIG. I.
  • the first coating is overcoated with a layer of aluminum. preferably ().l to 3.0 mils thick. by a physical vapor deposition technique already described and referred to in Powell et al. cited hereinabove.
  • the aluminum layer is deposited by evaporation from an electron beam heated source. This technique is particularly useful because the aluminum layer can be deposited in the same equipment used to deposit the MCrAl or MCrAlY by simply substituting an aluminum source for the MCrAl or MCrAlY source.
  • the coated body is subjected to a heat treatment to cause interdiffusion ofthe aluminum overlayer into the first coating layer.
  • a heat treatment to cause interdiffusion ofthe aluminum overlayer into the first coating layer.
  • the aluminum which has a low melting point of 660.2 C. diffuses into the cracks and defects of the first coating.
  • a simultaneous interdiffusion phenomena occurs during the heat treatment whereby the aluminum combines with the first coating to form a higher melting al loy.
  • the minimum temperature for the heat treatment is about 950 C. while the maximum temperature depends upon the superalloy substrate since it is undesirable to heat above the solutionizing heat treatment of the alloy involved. For nickel-base superalloys this tends to he in the range of about l040-l 230 C.
  • the heat treatment of cobalt-base alloys is much less complex than for nickel-base alloys and high temperature solution heat treatments are usually at about l l50 C.
  • the time of heat treatment is preferably in the range of about 0.25- hours.
  • the heat treatment should be performed in an inert atmosphere. e.g. helium. argon.
  • FIG. 2 A photomicrograph of a nickel-base superalloy which has been coated with a heat treated duplex coating of CoCrAlY plus aluminum is shown in FIG. 2.
  • the first coating of CoCrAlY exhibited tIaws or boundaries that are oriented in a perpendicular direction to the deposition plane as shown in FIG. I which become sites for attack by high temperature oxidation and corrosion as shown in FIG. 3.
  • FIG. 4 shows a photomicrograph of the heat treated duplex coating of (oCrAlY plus aluminum that has been subjected to a severe hot corrosion and oxidation environment consisting ofa fused salt at lo50 F. containing Na SO. and It is to this unique coating system that we attribute the improved properties of high temperature oxidation and corrosion resistance.
  • EXAMPLE 1 Ingredient Weight 1 ('oball o-l Chromium 22 Aluminum 13 Yttrium l Evaporation of the metal was at a constant power of 19.0 kilovolts and 275 milliamps for 30 minutes. A coating having a thickness of about 3 mils was deposited on the pins. The pins were cooled to room temperature in the vacuum. Then the chamber was filled to atmospheric pressure with air and a pure aluminum source was substituted for the CoCrAlY source. The chamber was again evacuated to a pressure of 10"" mm. Hg and the pins were overcoated with a layer of aluminum about V2 mil thick by evaporation at a constant power of 19.0 kilovolts and milliamps for three minutes. Finally. the pins coated with the duplex layer of (oCrAlY plus aluminum were heat treated for three hours at I C. in an argon atmosphere.
  • a crucible test was then performed to test resistance to oxidation and corrosion of the samples coated only with the CoCrAlY coating and the second group subjected to the duplex coating procedure. Both groups of coated pins were immersed in a fused salt bath of 85.2 percent Na- CO 0.5 percent NaCl. l3.0 percent V 0 and L3 percent Na SO (by weight) at a temperature of 900 C. in an air atmosphere. After 16 hours the samples were removed.
  • Comparative high temperature oxidation and corrosion tests were performed on test samples coated only with the NiCrAl alloy and on test samples coated with a heat treated duplex layer of NiCrAl plus aluminum. ln the crucible test. the pins were partially immersed in the fused salt mixture described in Example I for 16 hours at 900 C. The samples coated only with the Ni- CrAl coating after being subjected to the hot corrosion and oxidation test showed the typical corrosion and spike" penetration. The samples which had been protected by the heat treated duplex coating showed almost a complete absence of spike" corrosion and that indicated that the heat treated aluminum overlay coating had filled in the defects of the initial coating.
  • a method of improving the high temperature oxidation and corrosion resistance of a nickel-base or a cobalt-base superalloy body comprising the steps of:
  • composition consisting essentially in weight percent of 14-35 percent chromium. 4-20 percent aluminum. 0-3 percent yttrium and the balance being a member selected from the group consisting of iron. cobalt. nickel. and mixtures thereof.
  • composition consists essentially in weight percent of 25-2) percent chromium. l2l-l percent aluminum. 0().9 percent yttrium and the balance being iron.
  • composition consists essentially in weight percent of 19-24 percent chromium. l3l 7 percent aluminum. ()0.9 percent yttrium. and the balance being cobalt.
  • composition consisting essentially in weight percent of 20-35 percent chromium. 15-20 percent aluminum. 0-0.30 percent yttrium and the balance being nickel.

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Physical Vapour Deposition (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
US353660A 1973-04-23 1973-04-23 Coating system for superalloys Expired - Lifetime US3874901A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US353660A US3874901A (en) 1973-04-23 1973-04-23 Coating system for superalloys
NL7400370A NL7400370A (fr) 1973-04-23 1974-01-10
GB131874A GB1457033A (en) 1973-04-23 1974-01-11 Coating systems for superalloys
JP49019604A JPS501932A (fr) 1973-04-23 1974-02-20
IT21254/74A IT1009812B (it) 1973-04-23 1974-04-11 Perfezionato sistema di rivesti mento per superleghe
FR7413685A FR2226484B1 (fr) 1973-04-23 1974-04-19
DE2418879A DE2418879A1 (de) 1973-04-23 1974-04-19 Verbessertes beschichtungssystem fuer superlegierungen
BE143494A BE814053A (fr) 1973-04-23 1974-04-23 Procede de revetement de superalliages et pieces ainsi obtenues

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US353660A US3874901A (en) 1973-04-23 1973-04-23 Coating system for superalloys

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JP (1) JPS501932A (fr)
BE (1) BE814053A (fr)
DE (1) DE2418879A1 (fr)
FR (1) FR2226484B1 (fr)
GB (1) GB1457033A (fr)
IT (1) IT1009812B (fr)
NL (1) NL7400370A (fr)

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4218007A (en) * 1979-02-22 1980-08-19 General Electric Company Method of diffusion bonding duplex sheet cladding to superalloy substrates
US4326011A (en) * 1980-02-11 1982-04-20 United Technologies Corporation Hot corrosion resistant coatings
US4407871A (en) * 1980-03-25 1983-10-04 Ex-Cell-O Corporation Vacuum metallized dielectric substrates and method of making same
US4431711A (en) * 1980-03-25 1984-02-14 Ex-Cell-O Corporation Vacuum metallizing a dielectric substrate with indium and products thereof
GB2214934A (en) * 1987-10-09 1989-09-13 Kobe Steel Ltd Aluminium-chromium alloy vapour-deposited material
US4910092A (en) * 1986-09-03 1990-03-20 United Technologies Corporation Yttrium enriched aluminide coating for superalloys
US4933239A (en) * 1989-03-06 1990-06-12 United Technologies Corporation Aluminide coating for superalloys
US5236745A (en) * 1991-09-13 1993-08-17 General Electric Company Method for increasing the cyclic spallation life of a thermal barrier coating
US5384200A (en) * 1991-12-24 1995-01-24 Detroit Diesel Corporation Thermal barrier coating and method of depositing the same on combustion chamber component surfaces
US5500252A (en) * 1992-09-05 1996-03-19 Rolls-Royce Plc High temperature corrosion resistant composite coatings
US5807613A (en) * 1994-11-09 1998-09-15 Cametoid Advanced Technologies, Inc. Method of producing reactive element modified-aluminide diffusion coatings
US5837385A (en) * 1997-03-31 1998-11-17 General Electric Company Environmental coating for nickel aluminide components and a method therefor
US5987882A (en) * 1996-04-19 1999-11-23 Engelhard Corporation System for reduction of harmful exhaust emissions from diesel engines
US6422008B2 (en) 1996-04-19 2002-07-23 Engelhard Corporation System for reduction of harmful exhaust emissions from diesel engines
US6475647B1 (en) 2000-10-18 2002-11-05 Surface Engineered Products Corporation Protective coating system for high temperature stainless steel
US6537388B1 (en) 1996-08-23 2003-03-25 Alon, Inc. Surface alloy system conversion for high temperature applications
US6585864B1 (en) 2000-06-08 2003-07-01 Surface Engineered Products Corporation Coating system for high temperature stainless steel
US6635362B2 (en) 2001-02-16 2003-10-21 Xiaoci Maggie Zheng High temperature coatings for gas turbines
US6655369B2 (en) 2001-08-01 2003-12-02 Diesel Engine Transformations Llc Catalytic combustion surfaces and method for creating catalytic combustion surfaces
US20040157081A1 (en) * 2002-06-27 2004-08-12 Ji-Cheng Zhao High-temperature articles and method for making
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
EP1640477A3 (fr) * 2004-09-28 2006-08-16 Hitachi, Ltd. Composant au haute temperature ayant une barrière thérmique et turbine à gas
RU2283894C2 (ru) * 2005-01-13 2006-09-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Способ обработки поверхности металлического изделия
US7132130B1 (en) * 2005-05-20 2006-11-07 Innovative Systems Engineering Inc. Method for providing a chrome finish on a substrate
DE102005060243A1 (de) * 2005-12-14 2007-06-21 Man Turbo Ag Verfahren zum Beschichten einer Schaufel und Schaufel einer Gasturbine
US20070248457A1 (en) * 2006-04-25 2007-10-25 General Electric Company Rub coating for gas turbine engine compressors
US20090166204A1 (en) * 2002-09-11 2009-07-02 George Edward Creech Corrosion-resistant layered coatings
US20100196615A1 (en) * 2006-03-27 2010-08-05 Mitsubishi Heavy Industries, Ltd. Method for forming an oxidation-resistant film
US10023749B2 (en) * 2015-01-15 2018-07-17 United Technologies Corporation Method for nitride free vapor deposition of chromium coating
US10584411B2 (en) 2014-07-18 2020-03-10 United Technologies Corporation Chromium-enriched diffused aluminide
CN114008298A (zh) * 2019-06-20 2022-02-01 赛峰航空器发动机 涡轮发动机导向叶片涂覆方法及相关导向叶片
US11970953B2 (en) * 2019-08-23 2024-04-30 Rtx Corporation Slurry based diffusion coatings for blade under platform of internally-cooled components and process therefor
CN119980232A (zh) * 2025-04-15 2025-05-13 矿冶科技集团有限公司 一种抗氧化涂层及其制备方法、高温部件和航空设备

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US4101715A (en) * 1977-06-09 1978-07-18 General Electric Company High integrity CoCrAl(Y) coated nickel-base superalloys
DE3029488A1 (de) * 1980-08-02 1982-03-04 GHT Gesellschaft für Hochtemperaturreaktor-Technik mbH, 5060 Bergisch Gladbach Verfahren zur erzeugung einer schutzschicht auf metallischen werkstuecken
US4483720A (en) * 1981-11-27 1984-11-20 S R I International Process for applying thermal barrier coatings to metals
JPS59205468A (ja) * 1983-05-10 1984-11-21 Natl Res Inst For Metals 高温耐食性材料
JPS59184388U (ja) * 1983-05-27 1984-12-07 厚木自動車部品株式会社 インタ−ナルギヤポンプ
FR2672906A1 (fr) * 1991-02-19 1992-08-21 Grumman Aerospace Corp Revetement a barriere de diffusion pour alliages de titane.
RU2145363C1 (ru) * 1996-01-10 2000-02-10 Ставропольское высшее авиационное инженерное училище ПВО им.маршала авиации В.А.Судца Способ нанесения комбинированного жаростойкого покрытия
FR2757181B1 (fr) * 1996-12-12 1999-02-12 Snecma Procede de realisation d'un revetement protecteur a haute efficacite contre la corrosion a haute temperature pour superalliages, revetement protecteur obtenu par ce procede et pieces protegees par ce revetement
DE19960353A1 (de) * 1999-12-14 2001-06-21 Dechema Deutsche Gesellschaft Fuer Chemisches Apparatewesen, Chemische Technik Und Biotechnologie Ev Verfahren zur Herstellung einer Diffusionsbarriere zur Lebensdauererhöhung von Hochtemperatur-Schutzschichten
JP5281995B2 (ja) * 2009-09-24 2013-09-04 株式会社日立製作所 遮熱被覆を有する耐熱部材およびガスタービン
RU2419682C1 (ru) * 2010-03-02 2011-05-27 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") Состав для нанесения покрытий на детали диффузионным насыщением в газовой среде
JP6034034B2 (ja) * 2011-03-29 2016-11-30 ゼネラル・エレクトリック・カンパニイ 鋳造方法・材料及び装置、並びに該方法で製造される鋳造品

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US3594219A (en) * 1969-02-24 1971-07-20 United Aircraft Corp Process of forming aluminide coatings on nickel and cobalt base superalloys
US3640815A (en) * 1969-09-08 1972-02-08 Howmet Corp Method for surface treatment of nickel and cobalt base alloys
US3676085A (en) * 1971-02-18 1972-07-11 United Aircraft Corp Cobalt base coating for the superalloys

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3594219A (en) * 1969-02-24 1971-07-20 United Aircraft Corp Process of forming aluminide coatings on nickel and cobalt base superalloys
US3640815A (en) * 1969-09-08 1972-02-08 Howmet Corp Method for surface treatment of nickel and cobalt base alloys
US3676085A (en) * 1971-02-18 1972-07-11 United Aircraft Corp Cobalt base coating for the superalloys

Cited By (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4218007A (en) * 1979-02-22 1980-08-19 General Electric Company Method of diffusion bonding duplex sheet cladding to superalloy substrates
DE3006103A1 (de) * 1979-02-22 1980-09-04 Gen Electric Verfahren zum diffusionsverbinden eines doppelblechueberzuges mit einem substrat aus einer superlegierung
US4326011A (en) * 1980-02-11 1982-04-20 United Technologies Corporation Hot corrosion resistant coatings
US4407871A (en) * 1980-03-25 1983-10-04 Ex-Cell-O Corporation Vacuum metallized dielectric substrates and method of making same
US4431711A (en) * 1980-03-25 1984-02-14 Ex-Cell-O Corporation Vacuum metallizing a dielectric substrate with indium and products thereof
US4910092A (en) * 1986-09-03 1990-03-20 United Technologies Corporation Yttrium enriched aluminide coating for superalloys
GB2214934A (en) * 1987-10-09 1989-09-13 Kobe Steel Ltd Aluminium-chromium alloy vapour-deposited material
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JPS501932A (fr) 1975-01-10
DE2418879A1 (de) 1974-10-31
FR2226484A1 (fr) 1974-11-15
IT1009812B (it) 1976-12-20
NL7400370A (fr) 1974-10-25
GB1457033A (en) 1976-12-01
BE814053A (fr) 1974-08-16
FR2226484B1 (fr) 1977-10-14

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