US3528861A - Method for coating the superalloys - Google Patents

Method for coating the superalloys Download PDF

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Publication number
US3528861A
US3528861A US731649A US3528861DA US3528861A US 3528861 A US3528861 A US 3528861A US 731649 A US731649 A US 731649A US 3528861D A US3528861D A US 3528861DA US 3528861 A US3528861 A US 3528861A
Authority
US
United States
Prior art keywords
coating
base
percent
superalloys
cobalt
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.)
Expired - Lifetime
Application number
US731649A
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English (en)
Inventor
Richard C Elam
John A Petrusha
Frank P Talboom Jr
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.)
RTX Corp
Original Assignee
United Aircraft Corp
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Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
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Publication of US3528861A publication Critical patent/US3528861A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/08—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of copper or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • 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
    • C23C14/5886—Mechanical 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
    • C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
    • C23F17/00—Multi-step processes for surface treatment of metallic material involving at least one process provided for in class C23 and at least one process covered by subclass C21D or C22F or class C25
    • 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

Definitions

  • the present invention relates to improved methods of processing various alloys, particularly the nickel-base and cobalt-base superalloys, to provide a corrosion resistant coating thereon of long term durability.
  • a coating composition for the nickel-base and cobalt-base alloys which comprises iron, chromium, aluminum, and yttrium or a rare earth particularly at the composition, by weight, 20-50 percent chromium, 10-20 percent aluminum, 0.03-2 percent yttrium/rare earth, balance iron.
  • the present invention is particularly effective in eliminating the deterimental intergranular precipitate which has been found to occur during the deposition cycle of the coating process.
  • This invention describes an improved coating process for imparting long term corrosion resistance to various alloys, including the nickel-base and cobalt-base superalloys.
  • a cold-working/heat-treatment sequence to minimize the size and effect of any undesirable intergranular precipitate which may be formed in the deposition process.
  • coated articles are coldworked by shot peening, particularly glass bead blasting.
  • articles formed from the nickel-base and cobalt-base alloys are: coated with a composition comprising iron, chromium, aluminum and yttrium or a rare earth; heat treated following coating; cold-worked; and heat treated to effect recrystallization.
  • articles formed from the nickel-base and cobalt base superalloys are: coated in a vacuum chamber to a thickness of 0.003-0.005 inch with a composition comprising, by weight, 25-29 percent chromium, 12-14 percent aluminum, 0.6-0.9 percent yttrium, balance iron; following coating, the articles are heated to about 1900 F. for 4 hours in a non-oxidizing atmosphere, and cooled; the coated surfaces are dry glass bead peened; and, following peening the coated parts are held at about 1975 F. for 4 hours in a non-oxidizing atmosphere.
  • the present invention was developed primarily to increase the oxidation, sulfidation, erosion and thermal shock resistance of gas turbine blades and vanes formed of the nickel-base and cobalt-base superalloys.
  • the superalloys will be understood to be those strong, high temperature materials which find particular utility in the very demanding environments. Representative of these alloys are those identified in the industry as follows:
  • Alloy Composition (percent by weight) IN 10 Cr, 15 Co, 4.5 Ti, 5.5 A1, 3 Mo, .17 C, .75 V, .075 Zr, .015 B, balance Ni MAR-M200 9 or, 10 Co, 2 Ti, 5 A1, 12.5 w, .15 C, 1 Nb, .05 Zr, .015 B, balance
  • the characteristic of the typical superalloy is its basis as a nickel-chromium or cobalt-chromium solid solution with additions of aluminum, titanium and/or of refractory metals for strengthening, and carbon, boron and zironium to promote creep-rupture ductility.
  • the effect of the detrimental precipitate is eliminated with a corresponding increase in useful coating life by compressively stressing the coating through cold-working and subsequently heat treating the coating to cause recrystallization.
  • This treatment which is preferably performed utilizing shot peening or glass bead blasting, breaks up the precipitate into small particles which are more easily taken into solution by heat treatment and which are, in any event, more homogeneously distributed throughout the coating. Accordingly, exposure of the substrate to corrosive attack along the line of the intergranular precipitate is prevented.
  • the surfaces to be coated are first thoroughly cleaned free of all dirt, grease and other objectionable foreign matter, then conditioned by abrasive blasting followed by power flushing with clean water.
  • the coating is achieved by vapor deposition from a molten pool of the coating alloy in a vacuum chamber held at 10- Torr or better.
  • the melt chemistry is preferably of the following composition:
  • the parts are preheated in the vacuum chamber at 1750 F. for 5 minutes before deposition is commenced and maintained at temperature during coating. Deposition time varies somewhat but is controlled to obtain the preferred coating thickness for the exterior of blades and vanes of 0.003-0.005, excluding diffused zone. Subsequent cooling to below 1000 F. is accomplished in a non-oxidizing atmosphere at a rate equivalent to'air cooling. Following coating, the parts are heated to 1900 F. in vacuum; held at heat for 4 hours; and cooled in a non-oxidizing atmosphere at a rate equivalent to air coolmg.
  • coated surfaces are then dry glass bead peened using 0.007-0.011 inch diameter beads with an intensity equivalent to N, the peening being conducted in accordance with the provisions of the Aerospace Materials Specifications AMS 2430B.
  • the post-peening heat treatment involves heating to 1975 F. in dry argon, dry hydrogen or vacuum, holding at heat for 4 hours, and cooling at a rate equivalent to air cooling.
  • Blades and vanes so processed exhibit a uniform coatin-g having a thickness, excluding diffused zone, of 0.003- 0.005 inch.
  • the diffused zone for the nickel-base superalloys is 0.0010.002 inch and for the cobalt-base alloys 0.005-00015 inch.
  • the method of imparting high temperature corrosion resistance to the nickel-base and cobalt-base alloys which comprises the steps of coating the alloys with a composition consisting essentially of, by weight, 2050 percent chromium, 10-20 percent aluminum, 0.03-2 percent selected from the group consisting of yttrium and the rare earth elements, balance iron;
  • the coating consists essentially of, by weight, about 25-29 percent chromium, 12-14 percent aluminum, O.60.9 yttrium, balance iron, to a thickness of at least 0.003 inch.
  • composition consisting essentially of, by weight, 20-50 percent chromium, 10- 20 percent aluminum, 0.03-2 percent selected from the group consisting of yttrium and the rare earth elements, balance iron;
  • the coat ing consists essentially of, by weight, about 2529 percent chromium, 12-l4 percent aluminum, 0.6-0.9 percent yttrium, balance iron to a thickness of 0.0030.005 inch.
  • coating is accomplished by vapor deposition from a molten pool of the coating composition in a vacuum chamber.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physical Vapour Deposition (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
US731649A 1968-05-23 1968-05-23 Method for coating the superalloys Expired - Lifetime US3528861A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US73164968A 1968-05-23 1968-05-23

Publications (1)

Publication Number Publication Date
US3528861A true US3528861A (en) 1970-09-15

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Family Applications (1)

Application Number Title Priority Date Filing Date
US731649A Expired - Lifetime US3528861A (en) 1968-05-23 1968-05-23 Method for coating the superalloys

Country Status (7)

Country Link
US (1) US3528861A (enrdf_load_stackoverflow)
BE (1) BE732801A (enrdf_load_stackoverflow)
CH (1) CH540994A (enrdf_load_stackoverflow)
DE (1) DE1924092C2 (enrdf_load_stackoverflow)
FR (1) FR2010478B1 (enrdf_load_stackoverflow)
GB (1) GB1261261A (enrdf_load_stackoverflow)
SE (1) SE345145B (enrdf_load_stackoverflow)

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3951642A (en) * 1974-11-07 1976-04-20 General Electric Company Metallic coating powder containing Al and Hf
US3976436A (en) * 1975-02-13 1976-08-24 General Electric Company Metal of improved environmental resistance
US4071638A (en) * 1974-11-07 1978-01-31 General Electric Company Method of applying a metallic coating with improved resistance to high temperature to environmental conditions
US4086391A (en) * 1975-06-23 1978-04-25 United Technologies Corporation Alumina forming coatings containing hafnium for high temperature applications
US4151017A (en) * 1976-05-07 1979-04-24 Maschinenfabric Augsburg-Nurnberg Aktiengesellschaft Method of producing heat-resistant parts
US4168183A (en) * 1978-06-23 1979-09-18 University Of Delaware Process for improving the fatigue properties of structures or objects
FR2430461A1 (fr) * 1978-07-04 1980-02-01 Bulten Kanthal Ab Couche d'alliage obtenue par projection a chaud et son procede d'obtention
DE3229293A1 (de) * 1981-08-05 1983-03-24 United Technologies Corp., 06101 Hartford, Conn. Deckbelaege fuer superlegierungen
US4401697A (en) * 1980-01-07 1983-08-30 United Technologies Corporation Method for producing columnar grain ceramic thermal barrier coatings
US4405660A (en) * 1980-01-07 1983-09-20 United Technologies Corporation Method for producing metallic articles having durable ceramic thermal barrier coatings
US4405659A (en) * 1980-01-07 1983-09-20 United Technologies Corporation Method for producing columnar grain ceramic thermal barrier coatings
US4414249A (en) * 1980-01-07 1983-11-08 United Technologies Corporation Method for producing metallic articles having durable ceramic thermal barrier coatings
WO1994001244A1 (en) * 1992-07-10 1994-01-20 Sandvik Ab Method of blasting cutting tool inserts and the resulting inserts
EP0676481A3 (enrdf_load_stackoverflow) * 1994-03-25 1995-11-15 Ngk Insulators Ltd
EP1160352A1 (en) * 2000-05-31 2001-12-05 ALSTOM Power N.V. Method of adjusting the size of cooling holes of a gas turbine component
EP1251191A1 (en) 2001-04-21 2002-10-23 ALSTOM (Switzerland) Ltd A method of repairing a ceramic coating
US6569492B2 (en) 2000-06-05 2003-05-27 Alstom Ltd Process for repairing a coated component
WO2003057944A2 (en) 2002-01-10 2003-07-17 Alstom Technology Ltd. Mcraly bond coating and method of depositing said mcraly bond coating
US20040079648A1 (en) * 2002-10-15 2004-04-29 Alstom (Switzerland) Ltd. Method of depositing an oxidation and fatigue resistant MCrAIY-coating
US20040108019A1 (en) * 2002-12-06 2004-06-10 Alstom Technology Ltd. Non-destructive testing method of determining the depletion of a coating
US6773753B2 (en) 2001-08-14 2004-08-10 Alstom Technology Ltd Process for treating a coated gas turbine part, and coated gas turbine part
US20040159376A1 (en) * 2002-12-06 2004-08-19 Alstom Technology Ltd Non-destructive testing method of determining the service metal temperature of a component
US20040159552A1 (en) * 2002-12-06 2004-08-19 Alstom Technology Ltd. Method of depositing a local MCrAIY-coating
US20040163583A1 (en) * 2002-12-06 2004-08-26 Alstom Technology Ltd. Method of depositing a local MCrAIY-coating
US20040234808A1 (en) * 2001-09-22 2004-11-25 Alexander Schnell Mcraly-coating
US20040244676A1 (en) * 2001-09-22 2004-12-09 Alexander Schnell Method of growing a mcraly-coating and an article coated with the mcraly-coating
DE10337019A1 (de) * 2003-08-12 2005-03-10 Alstom Technology Ltd Baden Verfahren zur Bearbeitung einer beschichteten Gasturbinenschaufel
US6924045B2 (en) 2001-05-25 2005-08-02 Alstom Technology Ltd Bond or overlay MCrAIY-coating
EP1752553A2 (en) 2005-08-04 2007-02-14 United Technologies Corporation Method for microstructure control of ceramic thermal spray coating
US20070160873A1 (en) * 2006-01-10 2007-07-12 United Technologies Corporation Thermal barrier coating compositions, processes for applying same and articles coated with same
EP1829984A1 (en) 2006-03-01 2007-09-05 United Technologies Corporation High Density Thermal Barrier Coating
US20070231589A1 (en) * 2006-04-04 2007-10-04 United Technologies Corporation Thermal barrier coatings and processes for applying same
US20080113217A1 (en) * 2006-01-10 2008-05-15 United Technologies Corporation Thermal barrier coating compositions, processes for applying same and articles coated with same
US20080113218A1 (en) * 2006-01-10 2008-05-15 United Technologies Corporation Thermal barrier coating compositions, processes for applying same and articles coated with same
EP1939326A2 (en) 2006-12-22 2008-07-02 United Technologies Corporation Process for preventing the formation of secondary reaction zone in susceptible articles, and articles manufactured using same
EP2014786A1 (en) 2007-07-11 2009-01-14 United Technologies Corporation Process for controlling fatigue debit of a coated article
US20100098923A1 (en) * 2006-10-05 2010-04-22 United Technologies Corporation Segmented abradable coatings and process (ES) for applying the same
US20100159149A1 (en) * 2008-12-24 2010-06-24 United Technologies Corporation Apparatus for reducing stress when applying coatings, processes for applying the same and their coated articles
US20120222961A1 (en) * 2010-12-30 2012-09-06 Michel Shawn Smallwood System, method, and apparatus for leaching cast components
CN111041436A (zh) * 2019-11-15 2020-04-21 中国科学院宁波材料技术与工程研究所 一种用于锆合金防护的Fe-Cr-Al-Y防护涂层及其制备方法和应用

Families Citing this family (6)

* Cited by examiner, † Cited by third party
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GB1397066A (en) * 1971-06-19 1975-06-11 Rolls Royce High temperature corrosion resistant alloys
GB1521293A (en) * 1975-03-06 1978-08-16 Secr Defence Production of alloys
US4253884A (en) * 1979-08-29 1981-03-03 Special Metals Corporation Treating nickel base alloys
US4253885A (en) * 1979-08-29 1981-03-03 Special Metals Corporation Treating nickel base alloys
DE4226272C1 (de) * 1992-08-08 1994-02-10 Mtu Muenchen Gmbh Verfahren zur Behandlung von MCrAlZ-Schichten und mit dem Verfahren hergestellte Bauteile
RU2375497C1 (ru) * 2008-05-26 2009-12-10 Петр Тимофеевич Коломыцев Способ нанесения защитного покрытия на детали из никелевых сплавов

Citations (3)

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US2683305A (en) * 1949-07-15 1954-07-13 Sintercast Corp Molybdenum coated article and method of making
US2871150A (en) * 1955-09-19 1959-01-27 Westinghouse Electric Corp Method of cladding molybdenum
US3034934A (en) * 1960-03-31 1962-05-15 Gen Electric Method for processing of refractory metals

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
US2683305A (en) * 1949-07-15 1954-07-13 Sintercast Corp Molybdenum coated article and method of making
US2871150A (en) * 1955-09-19 1959-01-27 Westinghouse Electric Corp Method of cladding molybdenum
US3034934A (en) * 1960-03-31 1962-05-15 Gen Electric Method for processing of refractory metals

Cited By (68)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3951642A (en) * 1974-11-07 1976-04-20 General Electric Company Metallic coating powder containing Al and Hf
US4071638A (en) * 1974-11-07 1978-01-31 General Electric Company Method of applying a metallic coating with improved resistance to high temperature to environmental conditions
US3976436A (en) * 1975-02-13 1976-08-24 General Electric Company Metal of improved environmental resistance
US4086391A (en) * 1975-06-23 1978-04-25 United Technologies Corporation Alumina forming coatings containing hafnium for high temperature applications
US4151017A (en) * 1976-05-07 1979-04-24 Maschinenfabric Augsburg-Nurnberg Aktiengesellschaft Method of producing heat-resistant parts
US4168183A (en) * 1978-06-23 1979-09-18 University Of Delaware Process for improving the fatigue properties of structures or objects
FR2430461A1 (fr) * 1978-07-04 1980-02-01 Bulten Kanthal Ab Couche d'alliage obtenue par projection a chaud et son procede d'obtention
US4401697A (en) * 1980-01-07 1983-08-30 United Technologies Corporation Method for producing columnar grain ceramic thermal barrier coatings
US4405660A (en) * 1980-01-07 1983-09-20 United Technologies Corporation Method for producing metallic articles having durable ceramic thermal barrier coatings
US4405659A (en) * 1980-01-07 1983-09-20 United Technologies Corporation Method for producing columnar grain ceramic thermal barrier coatings
US4414249A (en) * 1980-01-07 1983-11-08 United Technologies Corporation Method for producing metallic articles having durable ceramic thermal barrier coatings
DE3229293A1 (de) * 1981-08-05 1983-03-24 United Technologies Corp., 06101 Hartford, Conn. Deckbelaege fuer superlegierungen
US6132293A (en) * 1992-07-10 2000-10-17 Sandvik Ab Method of blasting cutting tool inserts
WO1994001244A1 (en) * 1992-07-10 1994-01-20 Sandvik Ab Method of blasting cutting tool inserts and the resulting inserts
EP0676481A3 (enrdf_load_stackoverflow) * 1994-03-25 1995-11-15 Ngk Insulators Ltd
EP1160352A1 (en) * 2000-05-31 2001-12-05 ALSTOM Power N.V. Method of adjusting the size of cooling holes of a gas turbine component
US6623790B2 (en) * 2000-05-31 2003-09-23 Alstom (Switzerland) Ltd Method of adjusting the size of cooling holes of a gas turbine component
US6569492B2 (en) 2000-06-05 2003-05-27 Alstom Ltd Process for repairing a coated component
EP1251191A1 (en) 2001-04-21 2002-10-23 ALSTOM (Switzerland) Ltd A method of repairing a ceramic coating
US6890587B2 (en) 2001-04-21 2005-05-10 Alstom Technology Ltd Method of repairing a ceramic coating
US6924045B2 (en) 2001-05-25 2005-08-02 Alstom Technology Ltd Bond or overlay MCrAIY-coating
US6773753B2 (en) 2001-08-14 2004-08-10 Alstom Technology Ltd Process for treating a coated gas turbine part, and coated gas turbine part
US7094475B2 (en) 2001-09-22 2006-08-22 Alstom Technology Ltd MCrAlY-coating
US20040234808A1 (en) * 2001-09-22 2004-11-25 Alexander Schnell Mcraly-coating
US20040244676A1 (en) * 2001-09-22 2004-12-09 Alexander Schnell Method of growing a mcraly-coating and an article coated with the mcraly-coating
US7014923B2 (en) 2001-09-22 2006-03-21 Alstom Technology Ltd Method of growing a MCrAlY-coating and an article coated with the MCrAlY-coating
US7264887B2 (en) 2002-01-10 2007-09-04 Alstom Technology Ltd. MCrAlY bond coating and method of depositing said MCrAlY bond coating
US20070281103A1 (en) * 2002-01-10 2007-12-06 Alstom Technology Ltd MCrAIY BOND COATING AND METHOD OF DEPOSITING SAID MCrAIY BOND COATING
US20050003227A1 (en) * 2002-01-10 2005-01-06 Alstom Technology Ltd MCrAIY bond coating and method of depositing said MCrAIY bond coating
WO2003057944A2 (en) 2002-01-10 2003-07-17 Alstom Technology Ltd. Mcraly bond coating and method of depositing said mcraly bond coating
US20040079648A1 (en) * 2002-10-15 2004-04-29 Alstom (Switzerland) Ltd. Method of depositing an oxidation and fatigue resistant MCrAIY-coating
US7150798B2 (en) 2002-12-06 2006-12-19 Alstom Technology Ltd. Non-destructive testing method of determining the service metal temperature of a component
US20040163583A1 (en) * 2002-12-06 2004-08-26 Alstom Technology Ltd. Method of depositing a local MCrAIY-coating
US20040159552A1 (en) * 2002-12-06 2004-08-19 Alstom Technology Ltd. Method of depositing a local MCrAIY-coating
US7175720B2 (en) 2002-12-06 2007-02-13 Alstom Technology Ltd Non-destructive testing method of determining the depletion of a coating
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Also Published As

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BE732801A (enrdf_load_stackoverflow) 1969-10-16
CH540994A (de) 1973-08-31
DE1924092B1 (de) 1970-07-30
GB1261261A (en) 1972-01-26
FR2010478A1 (enrdf_load_stackoverflow) 1970-02-20
DE1924092C2 (de) 1971-03-04
FR2010478B1 (enrdf_load_stackoverflow) 1974-06-14
SE345145B (enrdf_load_stackoverflow) 1972-05-15

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