US3928026A - High temperature nicocraly coatings - Google Patents

High temperature nicocraly coatings Download PDF

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Publication number
US3928026A
US3928026A US469186A US46918674A US3928026A US 3928026 A US3928026 A US 3928026A US 469186 A US469186 A US 469186A US 46918674 A US46918674 A US 46918674A US 3928026 A US3928026 A US 3928026A
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nickel
cobalt
base
coating
essentially
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US469186A
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Ralph J Hecht
George W Goward
Richard C Elam
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Raytheon Technologies Corp
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United Technologies Corp
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Priority to US469186A priority Critical patent/US3928026A/en
Priority to CA220,942A priority patent/CA1045421A/en
Priority to CH498775A priority patent/CH606454A5/xx
Priority to IL47181A priority patent/IL47181A/en
Priority to DE2520192A priority patent/DE2520192C2/de
Priority to FR7514277A priority patent/FR2271299B1/fr
Priority to SE7505339A priority patent/SE410476B/xx
Priority to JP50055366A priority patent/JPS5919977B2/ja
Priority to IT23242/75A priority patent/IT1038126B/it
Priority to GB20193/75A priority patent/GB1489796A/en
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    • 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
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/052—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 40%
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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.]
    • 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
    • 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
    • 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.]
    • Y10T428/12986—Adjacent functionally defined components

Definitions

  • the present invention relates to coatings and coated articles and more particularly to coatings for the nickeland cobalt-base superalloys having high ductility while retaining desirable stability and elevated temperature oxidation and hot corrosion resistance.
  • Aluminide coatings can be, for example, a source of fracture initiation in fatigue. Coating ductility has been found to be an important determinant in fatigue life since at relatively low temperatures aluminide coatings tend to crack in a brittle manner at low strains in the tensile portions of the fatigue cycle.
  • the present invention relates to a nickelcobalt-chromium-aluminum-yttrium coating alloy having greatly improved ductility as well as other properties which together render it eminently suitable for use in gas turbine engine hardware and other rigorous environments.
  • the invention more particularly relates to a high ductility coating alloy which possesses both oxidation-erosion and sulfidation resistance and which consists of a particular combination of nickel, cobalt, chromium, aluminum and a reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and the other rare earth elements.
  • the invention contemplates a coating composition consisting essentially of, by weight, 1 1-48% cobalt, 1()-40% chromium, 9-15% aluminum, 0.01-1.0% of a reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and other rare earth elements, balance essentially nickel, the nickel content being at least about 15%.
  • the coating composition consists essentially of, by weight, about 15-40% cobalt, 12-30% chromium, -15% aluminum, 001-1 .0% yttrium, balance essentially nickel, the nickel content being at least about 15%.
  • the coating composition consists essentially of, by weight, about 25-40% cobalt, 14-22% chromium, 13-15% aluminum, 0.01-1.0% yttrium, balance essentially nickel.
  • the coating composition consists essentially of, by weight, about 1535% cobalt, 1422% chromium, 10l3% aluminum, 0.0ll'.0% yttrium, balance essentially nickel.
  • FIG. 1 is a graph which dramatically illustrates the ductility behavior of various nickel-cobalt-chromiumaluminum-yttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
  • FIG. 2 is a graph showing ductility as a function of temperature of some NiCoCrAlY coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
  • FIG. 3 is a graph illustrating the diffusional stability of various nickel-cobalt-chromium-aluminum-yttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
  • FIG. 4 is a graph illustrating the oxidation characteristics of various nickel-cobaIt-chromium-aluminumyttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
  • FIG. 5 is a graph illustrating the sulfidation characteristics of various nickel-cobaIt-chromium-aluminumyttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
  • the CoCrAlY and NiCrAlY coatings have provided significant improvements in the lifetimes 'of the superalloys.
  • NiCrAlY coatings while providing extremely high oxidation resistance and diffusional stability required improvement in sulfidation resistance
  • CoCrAlY coatings while providing extremely-high sulfidation resistance required improvement in oxidation resistance and diffusional stability.
  • a variety of overlay coatings was evaluated.
  • NiCrAlY coatings While it had been known that certain of the useful NiCrAlY coatings exhibited a ductility higher than certain of the useful CoCrAlY coatings and it had been surmised therefore that a substitution of some nickel for the cobalt in the CoCrAlY composition might improve ductility, it was surprising and unexpected that the nickel-cobalt-chromium-aluminumyttrium system as defined above would provide a ductility improvement which was markedly superior to either the NiCrAlY or CoCrAlY.
  • Correlation of coating microstructure with coating chemistry indicates that, in the nickel-cobalt-chromium-aluminum-yttrium system herein described, desirable y B microstructures are obtained at a higher aluminum content, the increased stability of the y B microstructure caused by cobalt additions to NiCrAlY being the result ofa significant reduction of the amount of y (Ni Al) and a(chromium) phases which are pre cipitated at lower temperatures.
  • Parts are preferably preheated to 1750F i 50 for 5 to 6, minutes before deposition is initiated and this temperature is maintained throughout the coating operation. Deposition time varies'somewhat but is controlled to obtain the preferred coating thickness of 0003-0005 inch. Subsequent cooling to below 1000F is accomplished in a nonoxidizing atmosphere. Following the coating step, the parts may be heat treated for 1 hour at 1900F i 25 in vacuum to more fully bond the coating to the substrate and provide for easier peening.
  • the coated articles may be dry glass bead peened using 0007-001 1 inch diameter beads with an intensity equivalent to 19 N.
  • the peening is conducted in accordance with the provisions of the processing specification AMS 2430.
  • the parts may then be heated to 1975F i 25 in dry argon, dry hydrogen or vacuum; held at heat for 4 hours;.and cooled in the protective atmosphere at a rate equivalent to air cooling. Blades and vanes so processed exhibit a coating thickness, excluding the diffused zone of 0003-0005 inch.
  • FIG. 1 a graph is shown of the unexpected ductility behavior of various nickel-cobaltchromium-aluminum-yttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys. The results shown therein were obtained by measuring strain to fracture of coatings deposited on tensile specimens of appropriate superalloys.
  • Curve A is a plot showing the effects of substituting various amounts of cobalt for nickel in a NiCrAlY alloy having a nominal composition of, by weight, Ni- -19Cr-l4Al-O.5Y while Curve B is a plot showing the effects of substituting various amounts of cobalt for nickel in a NiCrAlY alloy having a nominal composition of, by weight, Ni-l 9Cr-l 2.5Al-0.5Y.
  • Ni- CoCrAlY, or CoNiCrAlY as the case may be, coating alloys have compositional ranges consisting essentially of, by weight, 11-48% Co, l040% Cr, 9l5% Al, 0.1-1.0% reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and the other rare earth elements, balance essentially nickel (at least about 15%), preferably l5-40% Co, 12-30% Cr, 10l5% Al, O.ll.0% Y, balance essentially Ni, the nickel content being at least about 15%, will be effective in this regard.
  • a generally, higher range of cobalt is preferred, a preferred coating consisting essentially of 25-40% Co, l4-22% Cr, l3-15% Al, 0.0l-l.0% Y, balance essentially Ni.
  • Curve B a generally lower range of cobalt is preferred, a preferred coating consisting essentially of 15-35% Co, l422% Cr, l0-l3% Al, 0.0l-0.1% Y.
  • ductility curves for selected coatings show ductility as a function of temperature and indicate the markedly superior tensile cracking resistance of the NiCoCrAlY coatings.
  • thermomechanical fatigue tests a directionally solidified specimen substrate of MAR- M200 (with hafnium) was coated with Ni-24Co-l6- Cr12.5Al-40.3Y and run on a thermomechanical fatigue machine which pushes and pulls the specimen in severe fatigue and temperature cycles which simulate the strain-temperature cycle of a cooled turbine blade.
  • a number of identical substrates were coated with Co-20Cr12Al-0.5Y and another number with a diffusion aluminide coating. Both the CoCrAlY and the diffusion aluminide coated specimens failed after approximately 1,000 cycles or less on the thermomechanical fatigue machine whereas the NiCoCrAlY coated specimen did not fail until after 1,925 cycles.
  • FIGS. 3-5 a comparison of the interdiffusional, oxidation resistance and corrosion resistance properties of various NiCoCrAlY alloy coatings is shown.
  • 3-5 mil coatings of NiCoCr- AlY alloy consisting essentially of the indicated amounts of cobalt, 18-21% Cr, 13-14% Al and 0.05-0.8% Y were vapor deposited onto B-l900 substrates as well as onto directionally solidified MAR- M200 (plus Hf) substrates (erosion bars).
  • the coated samples were aged 100 hours in air at the indicated temperature.
  • FIG. 3 the coated samples were aged 100 hours in air at the indicated temperature.
  • coated components were subjected to 2000F cyclic burner-rig oxidation tests (2000F, 29 minutes forced air cool, 1 minute, JP fuel used) for up to 2,100 hours (2,030 hours hot time).
  • coated components were treated under cyclic conditions (1 ,750F, 3 minutes 2000F, 2 minutes cool, 2 minutes) in a high velocity hot gas stream derived from the combustion of JP 5 jet fuel, with 35 ppm salt/air added.
  • the claimed NiCoCrAlY coatings while giving unexpectedly increased ductility also simultaneously give adjustable and satisfactory degrees of interdiffusion and oxidation and hot corrosii n resistance.
  • B-l900 Ni-base alloy erosion bars were coated with a 3-5 mil thick alloy having a composition, consisting essentially of, by weight, Co-20Ni-24Cr-1- 5Al0.75Y generally in accordance with the procedures outlined above.
  • the coated erosion bars were subjected to 62.5 hours of vane cyclic sulfidation testing (1750F, 3 minutes 2050F, 2 minutes cool, 2 minutes with 35 ppm artificial sea salt: air ingested after combustion and using JP 5 fuel).
  • the coatings exhibited a specific life of from 21.1-24.4 hours/mil and were comparable to Fe-27Cr-13Al-.75Y coatings which exhibited specific lifetimes of 22.2-27.9 hours/- mil.
  • EXAMPLE 6 A 3.6 mil coating of Co20Ni-24Cr-15Al-0.75Y was vapor deposited onto a MAR-M302 Co-base alloy erosion bar and subjected to a modified vane cyclic sulfidation test (1750F, 3 minutes 2150F, 2 minutes cool, 2 minutes with 35 ppm artificial sea salt: air ingested after combustion using JP 5 fuel) in order to evaluate diffusional stability combined with the very high temperature sulfidation. The coating had a failure time of 162 hours and a specific life of 45 hours/mil.
  • Coatings consisting essentiallyof Co-20Ni-20Cr-l- 2Al-0.5Y, Co20Ni16Cr-l6Al-0.5Y, Ni32.5Co-20- Cr-12Al-O.5Y and Co-20Cr-12Al-O.5Y were vapor deposited to thicknesses of 4.5-5.5 mil on Co-20Ni- -l 8Cr-2ThO alloy airfoil specimens. All coatings were essentially a two phase mixture of beta CoAl or (CoNi- )Al and gamma solid solution. The Co20Ni-16Cr-l- 6A1-0.5Y coatings were predominantly beta with a small volume percent solid solution gamma phase.
  • the beta phase was continuous and represented an undesirable structure because of its potential low strain-tocrack characteristics.
  • the Co-20Ni-20Cr-12Al-0.5Y and the Co-20Cr-12Al-0.5Y coatings also exhibited a continuous beta type structure but contained substantially more gamma.
  • the Ni-32.5Co20Cr-12Al-0.5Y had a desired two phase plus gamma structure with the gamma phase being the continuous matrix phase.
  • Additional airfoil shaped specimens of Co20Ni-l 8- Cr-2ThO were vapor deposition coated with Co20- Crl2Al-0.5Y, Co20Ni-20Cr-l2Al-0.5Y and Ni- -32.5Co-20Cr-12Al-0.5Y to a thickness of 4.5-5.5 mil using the same techniques and subjected to 1800F, 2000F, 2200F and 2400F isothermal oxidation testing, to 2200F cyclic oxidation testing (1750F, 3 minutes 2200F, 2 minutes cool, 2 minutes) and to 2200F cyclic hot corrosion testing (1750F, 3 minutes 2200F, 2 minutes cool, 2 minutes).
  • the 1800F and 2000F isothermal oxidation tests were discontinued at 214 and 222 hours, respectively. All specimens shows no visual signs of degradation. Based on metallographic examination of specimens from the 1800F tests, coating degradation was least for the Ni32.5Co-20Cr-12Al-0.5Y. Also in the 2000F test, the NiCoCrAlY coating exhibited the least degradation. The extent of degradation of the CoNiCrAlY and CoCrAlY coatings was approximately equal.
  • the 2400F isothermal oxidation test was run to coating failure.
  • the NiCoCrAlY composition exhibited the longest life, 226 hours.
  • the cyclic oxidation and-cyclic hot corrosion tests were discontinued at 207 (59 hours hot time) and 204 (58 hours hot time) hours, respectively. Coating failure had not occurred. Essentially no difference was observed in the structure between the three samples in the hot corrosion test. However, in the cyclic oxidation test, the Ni-32.5Co20Cr-l 2Al-0.5Y coating exhibited a far greater amount of retained beta than either of the other two.
  • EXAMPLES 15-16 In a series of especially severe engine tests, first stage turbine blades of the alloys indicated were coated as indicated in Table l and run for 297 hours including 2,000 cycles (acceleration to full takeoff power followed by holding for a period of time, rapid deceleration to idle power and holding for a period of time). Over 100 cycles were with water injection (for thrust augmentation) which imposed the severest possible thermal shock to the coatings.
  • nickel aluminum, 0.01-1.0% yttrium, balance essentially nickel, the nickel content being at least about 15%.
  • a coating composition for the nickel-base and cobalt-base alloys which consists essentially of, by weight, -40% cobalt, 14-22% chromium, 13-15% aluminum, 0.01-l.0% yttrium, balance essentially nickel.
  • a coating composition for the nickel-base and cobalt-base alloys which consists essentially of, by weight, 1535% cobalt, 14-22% chromium, 10-13% aluminum, 0.01-1.0% yttrium, balance essentially nickel.
  • a coating composition for the nickel-base and cobalt-base alloys which consists essentially of, by weight, 32.5% cobalt, 20% chromium, 12% aluminum, 0.5% yttrium, balance essentially nickel.
  • a coating composition for the nickel-base and cobalt-base alloys which consists essentially of, by weight, 20% nickel, 20% chromium, 12% aluminum, 0.5% yttrium, balance essentially cobalt.
  • inventive alloy coatings are effective not only in providing long term oxidation resistance, corrosion resistance and stability but dramatically improved ductility.
  • a coating composition for the nickel-base and cobalt-base alloys which consists essentially of, by weight, 1 1-48% cobalt, 10-40% chromium, 9-l5% aluminum, 0.01-1 .O% of a reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and other rare earth elements balance essentially nickel, the nickel content being at least about 15%.
  • a coating composition for the nickel-base and cobalt-base alloys which consist essentially of, by weight, 15-40% cobalt, 12-30% chromium, lO-l5% 7.
  • a gas turbine engine component comprising a nickel-base or cobalt-base superalloy coated to a thickness of at least about 0.003 inch with a coating consisting essentially of, by weight, 11-48% cobalt, l0-40% chromium, 9-l5% aluminum, 0.0l-l.0% of a reactive metal selected from the group consisting of yttrium, scandium, thorium and other rare earth elements, balance essentially nickel, the nickel content being at least about 15%.
  • a gas turbine engine component comprising a nickel-base or cobalt-base superalloy coated to a thickness of at least about 0.003 inch with a coating consisting essentially of, by weight, 1540% cobalt, l2-30% chromium, l0-15% aluminum, 0.01-1 0% yttrium, balance essentially nickel, the nickel content being at least about 15%.
  • a gas turbine engine component comprising a nickel-base or cobalt-base superalloy coated to a thickness of at least about 0.003 inch with a coating consisting essentially of, by weight 25-40% cobalt, 14-22% chromium, l3-l5% aluminum, 0.0l-l.0% yttrium, balance essentially nickel.
  • a gas turbine engine component comprising a nickel-base or cobalt-base superalloy coated to a thick ness of at least about 0.003 inch with a coating consisting essentially of, by weight, l5-35% cobalt, 14-22% chromium, 10-l3% aluminum, 0.0l1.0 yttrium, balance essentially nickel.

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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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Physical Vapour Deposition (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
US469186A 1974-05-13 1974-05-13 High temperature nicocraly coatings Expired - Lifetime US3928026A (en)

Priority Applications (10)

Application Number Priority Date Filing Date Title
US469186A US3928026A (en) 1974-05-13 1974-05-13 High temperature nicocraly coatings
CA220,942A CA1045421A (en) 1974-05-13 1975-02-24 High temperature nicocraly coatings
CH498775A CH606454A5 (US20030199744A1-20031023-C00003.png) 1974-05-13 1975-04-19
IL47181A IL47181A (en) 1974-05-13 1975-04-28 High temperature nicocraiy coatings
DE2520192A DE2520192C2 (de) 1974-05-13 1975-05-06 Verwendung von Nicocraly-Legierungen als Werkstoffe zum Beschichten von Superlegierungsgegenständen
FR7514277A FR2271299B1 (US20030199744A1-20031023-C00003.png) 1974-05-13 1975-05-07
SE7505339A SE410476B (sv) 1974-05-13 1975-05-07 Beleggningskomposition for legeringar baserade pa nickel eller kobolt samt gasturbinmotorkomponent belagd med kompositionen
JP50055366A JPS5919977B2 (ja) 1974-05-13 1975-05-07 高温Ｎｉ Ｃｏ Ｃｒ Ａｌ Ｙ 被覆組成物
IT23242/75A IT1038126B (it) 1974-05-13 1975-05-13 Composizione di rivestimento per superlaghe resistente alle alte temperature
GB20193/75A GB1489796A (en) 1974-05-13 1975-05-13 High temperature nicocraly coatings

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US469186A US3928026A (en) 1974-05-13 1974-05-13 High temperature nicocraly coatings

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US3928026A true US3928026A (en) 1975-12-23

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US (1) US3928026A (US20030199744A1-20031023-C00003.png)
JP (1) JPS5919977B2 (US20030199744A1-20031023-C00003.png)
CA (1) CA1045421A (US20030199744A1-20031023-C00003.png)
CH (1) CH606454A5 (US20030199744A1-20031023-C00003.png)
DE (1) DE2520192C2 (US20030199744A1-20031023-C00003.png)
FR (1) FR2271299B1 (US20030199744A1-20031023-C00003.png)
GB (1) GB1489796A (US20030199744A1-20031023-C00003.png)
IL (1) IL47181A (US20030199744A1-20031023-C00003.png)
IT (1) IT1038126B (US20030199744A1-20031023-C00003.png)
SE (1) SE410476B (US20030199744A1-20031023-C00003.png)

Cited By (81)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993454A (en) * 1975-06-23 1976-11-23 United Technologies Corporation Alumina forming coatings containing hafnium for high temperature applications
US4029477A (en) * 1975-10-29 1977-06-14 General Electric Company Coated Ni-Cr base dispersion-modified alloy article
FR2406000A1 (fr) * 1977-10-17 1979-05-11 United Technologies Corp Articles en superalliage de nickel, de cobalt et/ou de fer revetus, resistant a l'oxydation et a l'usure
US4198442A (en) * 1977-10-31 1980-04-15 Howmet Turbine Components Corporation Method for producing elevated temperature corrosion resistant articles
DE3010608A1 (de) * 1979-05-29 1980-12-11 Howmet Turbine Components Ueberzugszusammensetzung fuer nickel, kobalt und eisen enthaltende superlegierung und superlegierungskomponente
US4275090A (en) * 1978-10-10 1981-06-23 United Technologies Corporation Process for carbon bearing MCrAlY coating
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US11261742B2 (en) * 2013-11-19 2022-03-01 Raytheon Technologies Corporation Article having variable composition coating
US20220170379A1 (en) * 2013-11-19 2022-06-02 Raytheon Technologies Corporation Article having variable composition coating
US11834963B2 (en) * 2013-11-19 2023-12-05 Rtx Corporation Article having variable composition coating
WO2024036104A1 (en) 2022-08-09 2024-02-15 Praxair S.T. Technology, Inc. High performance alumina-forming multi- element materials for high temperature applications
CN115747795A (zh) * 2022-12-05 2023-03-07 江苏大学 一种高服役寿命的热障涂层粘结层及其制备方法
CN115747795B (zh) * 2022-12-05 2024-03-26 江苏大学 一种高服役寿命的热障涂层粘结层及其制备方法

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SE410476B (sv) 1979-10-15
DE2520192A1 (de) 1975-11-27
IL47181A (en) 1977-07-31
GB1489796A (en) 1977-10-26
CH606454A5 (US20030199744A1-20031023-C00003.png) 1978-10-31
DE2520192C2 (de) 1986-02-06
IT1038126B (it) 1979-11-20
SE7505339L (sv) 1975-11-14
FR2271299A1 (US20030199744A1-20031023-C00003.png) 1975-12-12
JPS5919977B2 (ja) 1984-05-10
JPS50158531A (US20030199744A1-20031023-C00003.png) 1975-12-22
FR2271299B1 (US20030199744A1-20031023-C00003.png) 1978-06-09
IL47181A0 (en) 1975-08-31
CA1045421A (en) 1979-01-02

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