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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Effectivness of yttrium, lanthanum, and hafnium coatings for preventing nitridation embrittlement of chromium alloys at high temperatures
Aluminum protective coatings for chromium alloys
Friction wear of human hip joint prostheses made from cobalt molybdenum and cobalt molybdenum chromium alloys
A dispersion-strengthened alloy, TD nickel chromium (TDNiCr) is being developed for use on the thermal protection system of the space shuttle at temperatures up to 1204 C(2200 F). Manufacturing processes were developed for the fabrication of sheet and foil to specifications. The addition of aluminum to the basic TDNiCr composition provides outstanding oxidation resistance up to 1260 C(2300 F); aluminum levels of 2 to 4% are considered optimum for space shuttle application.
Self-lubricating properties of composites of porous nickel and nickel-chromium alloy impregnated with barium fluoride-calcium flouride eutectic
Self-lubricating composite materials prepared by vacuum impregnating nickel-chromium alloy with barium fluoride-calcium fluoride eutectic composition
Chromium and chromium rhenium alloys tested for tensile properties and strain aging
Reduction of ductile-to-brittle transition temperature for unalloyed chromium achieved in alloys resembling Cr-Re system
Chemical vapor deposition process for production of high purity chromium metal containing thorium oxide dispersion material
Determining mechanical properties and air-oxidation behavior of chromium-base compositions at temperatures up to 2400 F
Finely divided powder mixture produced by vapor deposition of CR on small ThO2 particles was hot pressed or pressure bonded. Resulting alloy has lower ductile-to-brittle transition temperature than pure chromium, and high strength and oxidation resistance at elevated temperatures, both in as-rolled condition and after annealing.
Two dispersion strengthened nickel base alloy systems were developed for use at temperatures up to 1204 C(2200 F); TD nickel chromium (TDNiCr) and TD nickel chromium aluminum (TDNiCrA1). They are considered candidate materials for use on the thermal protection systems of the space shuttle and for long term use in aircraft gas turbine engine applications. Improved manufacturing processes were developed for the fabrication of TDNiCr sheet and foil to specifications. Sheet rolling process studies and extrusion studies were made on two aluminum containing alloys: Ni-16%Cr-3.5%A1-2%ThO2 and Ni-16%Cr-5.0%A12%ThO2. Over 1600 kg.(3500 lb.) of plate, sheet, foil, bar and extrusion products were supplied to NASA Centers for technology studies.
Fabrication of Cr-Mo-Ta-C-Y alloy sheet
Ductile metal clads and coatings of silicides, aluminides and noble metals to protect Cr alloys against nitrogen embrittlement and air oxidation
Silicide, aluminide and boride coatings transition temperature holdability, considering nitridation/ oxidation protection for Cr alloys
Cr alloys applications in high temperature environments, describing alloying elements effects on strength and ductility
Dispersion strengthened Ni-Cr alloys creep properties, investigating temperature, applied stress and thorium dioxide particles effects
Thoria dispersed Ni-Cr alloy hypersonic entry ablation model, accounting for Cr oxidation