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  • 1
    facet.materialart.
    Unknown
    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
  • 2
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    Thermal barrier coatings for heat engine components (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A comprehensive NASA-Lewis program of coating development for aircraft gas turbine blades and vanes is presented. Improved ceramic layer compositions are investigated, along the MCrAlY bond films and the methods of uniform deposition of the coatings; the thermomechanical and fuel impurity tolerance limits of the coatings are being studied. Materials include the ZrO2-Y2O3/NiCrAlY system; the effects of the bond coat and zirconia composition on coating life and Mach 1 burner rig test results are discussed. It is concluded that Diesel engines can also utilize thermal barrier coatings; they have been used successfully on piston crowns and exhaust valves of shipboard engines to combat lower grade fuel combustion corrosion.
    Keywords: METALLIC MATERIALS
    Type: SAMPE Quarterly; 12; Oct. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Surface protection (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The surface protection subproject consists of three major thrusts: airfoil deposition model; metallic coating life prediction; and thermal barrier coating (TBC) life prediction. The time frame for each of these thrusts and the expected outputs are presented. Further details are given for each thrust such as specific element schedules and the status of performance; in-house, via grant, or via contract.
    Keywords: METALLIC MATERIALS
    Type: Turbine Engine Hot Section Technology, 1984; 10 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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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
  • 5
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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
  • 6
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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
  • 7
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    Corrosion resistant thermal barrier coating (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A thermal barrier coating system for protecting metal surfaces at high temperature in normally corrosive environments is described. The thermal barrier coating system includes a metal alloy bond coating, the alloy containing nickel, cobalt, iron, or a combination of these metals. The system further includes a corrosion resistant thermal barrier oxide coating containing at least one alkaline earth silicate. The preferred oxides are calcium silicate, barium silicate, magnesium silicate, or combinations of these silicates.
    Keywords: METALLIC MATERIALS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal barrier coatings for superalloys (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The current status of ceramic thermal barrier coatings for protection of turbine airfoil components is reviewed. Test results for an early duplex coating system ZrO2-12% Y2O3/Ni-16% Cr-6% Al-0.6% Y, improved system ZrO2-8% Y2O3/Ni-17% Cr-5% Al-0.35% Y, and air/fuel impurity tolerant systems based on ZrO2-8% Y2O3, 2CaO-SiO2, and a MgO-NiCrAlY cermet are discussed. Preliminary test results at 800 C for a graded ZrO2-8% Y2O3/Ni-20% Cr-11% Al-0.4% Y coating system show that the coating can survive at least 500 hr in the presence of 50 ppm V plus other fuel contaminants and additives.
    Keywords: METALLIC MATERIALS
    Type: International Symposium on Superalloys 1980; Sep 21, 1980 - Sep 25, 1980; Champion, PA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Advanced aircraft engine materials trends (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Recent activities of the Lewis Research Center are reviewed which are directed toward developing materials for rotating hot section components for aircraft gas turbines. Turbine blade materials activities are directed at increasing metal temperatures approximately 100 C compared to current directionally solidified alloys by use of oxide dispersion strengthening or tungsten alloy wire reinforcement of nickel or iron base superalloys. The application of thermal barrier coatings offers a promise of increasing gas temperatures an additional 100 C with current cooling technology. For turbine disk alloys, activities are directed toward reducing the cost of turbine disks by 50 percent through near net shape fabrication of prealloyed powders as well as towards improved performance. In addition, advanced alloy concepts and fabrication methods for dual alloy disks are being studied as having potential for improving the life of future high performance disks and reducing the amount of strategic materials required in these components.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-82626 , E-879 , Ann. Intern. Gas Turbine Conf.; Mar 08, 1981 - Mar 12, 1981; Houston, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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