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  • 1
    facet.materialart.
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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
  • 2
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    Effect of fuel to air ratio on Mach 0.3 burner rig hot corrosion of ZrO2-Y2O3 thermal barrier coatings (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A Mach 0.3 burner rig test program was conducted to determine how the fuel to air mass ratio affects the durability of ZrO2-Y2O3/Ni-16Cr-6Al-0.31Y thermal barrier coating systems in combustion products containing 5 ppm Na and 2 ppm V. As the fuel to air mass ratio was increased from 0.039 to 0.049, the durability of ZrO2-6Y2O3, ZrO2-8Y2O3 and ZrO2-12Y2O3 coatings decreased. ZrO2-8Y2O3 coatings were approximately 2X and 1.3X more durable than ZrO2-12Y2O3 and ZrO2-6Y2O3 coatings respectively at the fuel to air mass ratio of 0.039. The number of one hour cycles endured by ZrO2-8Y2O3 coatings varied from averages of 53 to 200 for the fuel to air mass ratios of 0.049 and 0.039, respectively. At the fuel to air mass ratio of 0.049, all ZrO2-Y2O3 coated specimens failed in 40 to 60 one hour cycles
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-82879 , E-1255 , DOE/NASA/10350-32 , NAS 1.15:82879
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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
  • 4
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    Thermal barrier coatings: Burner rig hot corrosion test results (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    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 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 volume percent MgO-50 volume percent 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: METALLIC MATERIALS
    Type: NASA-TM-79005 , E-9787 , DOE/NASA/2593-78/3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Evaluation of hot corrosion behavior of thermal barrier coatings (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Calcium silicate and yttria stabilized zirconia/MCrAlY thermal barrier coating systems on air-cooled specimens were exposed to sodium plus vanadium doped Mach 0.3 combustion gases. Thermal barrier coating endurance was determined to be a strong inverse function of ceramic coating thickness. Coating system durability was increased through the use of higher Cr + Al NiCrAl and CoCrAlY bond coatings. Chemical and electron microprobe analyses supported the predictions of condensate compositions and the determination of their roles in causing spalling of the ceramic coatings.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-81520 , DOE/NASA/2593-16 , Intern. Conf. on Met. Coatings; Apr 21, 1980 - Apr 25, 1980; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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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
  • 7
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    Review of NASA progress in thermal barrier coatings for stationary gas turbines (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Ceramic thermal barrier coatings for industrial/utility gas turbines were investigated. In burner rig tests of a zirconia yttria/nickel chromium aluminum yttrium ZrO2-12w/0Y2O3/NiCrAlY coating system on air cooled superalloy specimens, ceramic coating life (spallation) was sensitive to Na and V concentration in the fuel. The locations of coating spallation correspond to areas where combustion products were predicted to condense. Three new thermal barrier coating systems were identified. These are based on calcium silicate, ZrO2-8w/0Y2O3, and a MgO-NiCrAlY cermet. The spall resistance can be increased by reducing the ceramic layer thickness from 0.038 to 0.013 cm and by the use of more oxidation/corrosion resistant bond coats.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-81716 , DOE/NASA/2593-25 , E-749 , Intern. Gas Turbine Conf.; Mar 09, 1981 - Mar 12, 1981; Houston, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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