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  • 1
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    External Symmetry of Cobalt Particles Produced by Hydrogen Reduction of CoBr2 (1964)
    American Institute of Physics
    Details
    Publication Date: 1964-07-01
    Print ISSN: 0021-8979
    Electronic ISSN: 1089-7550
    Topics: Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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    Aluminized alloy boosts turbine blade life (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Description of an aluminized alloy coating technique that involves first the application of a ductile, oxidation-resistant overlay, such as NiCrAl, which is then partially aluminized. The duplex protective system has performance advantages over conventional aluminide coatings in that it provides higher-temperature hot corrosion resistance over a longer service life.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: Metal Progress; 106; Aug. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Oxidation resistant claddings for superalloys. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The oxidation protection afforded IN-100 and WI-52 superalloys by thin claddings of NiCrAlSi and FeCrAlY alloys was examined primarily at 1090 C. Comparisons were made with commercial aluminide coatings, using cyclic furnace and high-velocity burner rig tests. In furnace tests, NiCrAlSi on IN-100 and FeCrAlY on WI-52 performed as well as or better than two aluminide coatings. Burner rig performance of the FeCrAlY cladding was better than that of the NiCrAlSi cladding on IN-100 and the aluminide coating on WI-52, but less than the aluminide coating on IN-100. An aluminized NiCrAlSi cladding performed better than any coating or cladding.
    Keywords: MATERIALS, METALLIC
    Type: Metals Engineering Quarterly; 12; May 1972
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A new diffusion-inhibited oxidation-resistant coating for superalloys (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously announced in STAR as N81-33273)
    Keywords: METALLIC MATERIALS
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Coating Life Prediction (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Hot-section gas-turbine components typically require some form of coating for oxidation and corrosion protection. Efficient use of coatings requires reliable and accurate predictions of the protective life of the coating. Currently engine inspections and component replacements are often made on a conservative basis. As a result, there is a constant need to improve and develop the life-prediction capability of metallic coatings for use in various service environments. The purpose of this present work is aimed at developing of an improved methodology for predicting metallic coating lives in an oxidizing environment and in a corrosive environment.
    Keywords: NONMETALLIC MATERIALS
    Type: Turbine Engine Hot Section Technology, 1984; 12 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Overlay metallic-cermet alloy coating systems (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A substrate, such as a turbine blade, vane, or the like, which is subjected to high temperature use is coated with a base coating of an oxide dispersed, metallic alloy (cermet). A top coating of an oxidation, hot corrosion, erosion resistant alloy of nickel, cobalt, or iron is then deposited on the base coating. A heat treatment is used to improve the bonding. The base coating serves as an inhibitor to interdiffusion between the protective top coating and the substrate. Otherwise, the protective top coating would rapidly interact detrimentally with the substrate and degrade by spalling of the protective oxides formed on the outer surface at elevated temperatures.
    Keywords: METALLIC MATERIALS
    Type: NAS 1.71:LEW-13639-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Coating with overlay metallic-cermet alloy systems (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A base layer of an oxide dispersed, metallic alloy (cermet) is arc plasma sprayed onto a substrate, such as a turbine blade, vane, or the like, which is subjected to high temperature use. A top layer of an oxidation, hot corrosion, erosion resistant alloy of nickel, cobalt, or iron is then arc plasma sprayed onto the base layer. A heat treatment is used to improve the bonding. The base layer serves as an inhibitor to interdiffusion between the protective top layer and the substrate. Otherwise, the 10 protective top layer would rapidly interact detrimentally with the substrate and degrade by spalling of the protective oxides formed on the outer surface at elevated temperatures.
    Keywords: METALLIC MATERIALS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A new diffusion-inhibited oxidation-resistant coating for superalloys (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A concept for enhanced protection of superalloys consists of adding an oxidation- and diffusion-resistant cermet layer between the superalloy and the outer oxidation-resistant metallic alloy coating. Such a duplex coating was compared with a physical-vapor-deposited (PVD) NiCrAlY coating in cyclic oxidation at 1150 C. The substrate alloy was MA 754 - an oxide-dispersion-strengthened superalloy that is difficult to coat. The duplex coating, applied by plasma spraying, outperformed the PVD coating on the basis of weight change and both macroscopic and metallographic observations.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-82687 , E-968
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Improved bond coatings for use with thermal barrier coatings (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The potential for improving the durability of thermal barrier coatings (TBC's) being developed for coal derived fuel fired gas turbines was studied. Furnace oxidation behavior of plasma deposited bond coatings was improved by increasing the thickness from 0.010 cm to 0.015 cm and by depositing the coatings at 20 kW with argon 3.5 vol % hydrogen arc gas rather than at 11 kW with argon. The most oxidation resistant plasma deposited bond coatings were Ni-14, 1Cr-13.4Al-0.10Zr, Ni-14.3Cr-14.4Al.0.16Y, and Ni-15.8Cr-12.8Al-0.36Y on B-1900 + Hf and Ni-30.9Cr-11.1Al-0.48Y on MAR-M-509. The oxidation resistant bond coatings improved TBC life when the coatings were deposited on the specimens supported on a nail bed fixture during coating.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-81567 , DOE/NASA/2593-18 , E-532
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Thermal barrier coatings - Burner rig hot corrosion test results (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A Mach 0.3 burner rig test program was conducted to examine the sensitivity of thermal barrier coatings to Na- and V-contaminated combustion gases simulating potential utility gas turbine environments. Coating life of the standard ZrO2-12Y2O3/Ni-16.2Cr-5.6Al-0.6Y (composition in wt %) NASA thermal barrier coating system which was developed for aircraft gas turbines was significantly reduced in such environments. Two thermal barrier coating systems, Ca2SiO4/Ni-16.2Cr-5.6Al-0.6Y and ZrO2-8Y2O3/Ni-16.4Cr-5.1Al-0.15Y and a less insulative cermet coating system, 50 vol % MgO-50 vol % Ni-19.6Cr-17.1Al-0.97Y/Ni-16.2Cr-5.6Al-0.6Y, were identified as having much improved corrosion resistance compared to the standard coating.
    Keywords: NONMETALLIC MATERIALS
    Type: Journal of Materials for Energy Systems; 1; Mar. 198
    Format: text
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    NASA TECHNICAL REPORTS
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