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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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Cobalt-base alloy which combines high temperature strength and magnetic properties has a composition in weight percent of 7-1/2 tungsten, 2-1/2 iron, 1 titanium, 1/2 zirconium, 1/2 carbon, and the balance cobalt. It may be used as construction material for electric motors and generators operating at high temperatures.
Chemically bonded zirconium oxides strengthened with silicon carbide whiskers
Effects of various energy environments on zirconium-oxygen-carbon system, solid state ceramics, surface properties, and ceramic materials processing
Optimum parameters of hot extrusion of calcium, magnesium, and zirconium oxides
Zirconium oxide loadings and coating methods varied to improve separators for heat sterilizable battery
Electrical, and calorimetric measurements on alternating current loss in niobium zirconium, niobium titanium, and niobium stannide superconductors
Operational characteristics of two loop lithium boiling potassium system of niobium zirconium Rankine cycle test loop
Process developed for brazing niobium-zirconium alloys for heat exchanger tube fabrication
Thermal conductivity, insulation, and thermal shock qualities of zirconium coatings on Hastelloy
Electrochemical properties of zirconium phosphate membranes containing zeolites related to independent electrolysis, fuel cell operation and regenerative fuel cell cycle
Critical surfaces for niobium stannides ribbon and niobium zirconium wire
High emittance coating materials for beryllium, niobium-zirconium compounds, and stainless steel used in spacecraft radiators
Anti-wettable materials brazing processes using titanium and zirconium for surface pretreatment
Zirconium-based alloy brazing of internal fins of Cb-1Zr foil to Cb-1Zr heat receiver tubes
Zirconium dioxide chromium alloy powder dispersions
Various refractory coating systems were evaluated for rocket nozzle applications by actual rocket test firings. A reference is noted which identifies failure mechanisms and gives results of the firing tests for 18 coating systems. Iridium, iridium-rhenium, and hafnium oxide-zirconium oxide coatings show most promising results.
Test conditions and results are reported for various coatings on a 1 percent zirconium columbium alloy at a temperature of 2000 deg F. Molybdenum silicide over molybdenum is most effective coating, tin-aluminum coating is adequately protective, chromium-molybdenum silicides are not protective.
Wire reinforced zirconium oxide rocket nozzle inserts