A Study of Several Oxidation-resistant Coatings on Mo-0.5Ti Alloy Sheet at 2,500 ̊F
National Aeronautics and Space Administration, 1964 - Molybdenum - 78 pages
The results are presented of a study of several silicide-base oxidation-resistant coatings applied to 0.012-inch-thick molybdenum-alloy sheet. The specimens were both continuously and cyclically exposed at 2,500 degrees F in air. The effect of three different types of thermal cycles was investigated. A failure mechanism is proposed to explain the severe reduction observed in the ability of a coating to protect the substrate when thermally cycled. A failure mechanism for the continuously exposed coated specimens is also proposed. The investigation includes the results of X-ray studies and room-temperature mechanical-property tests on the coated specimens.
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0xidation 1.0-hour cycles 10-percent weight loss As-coated appearance as-coated specimens as-coated surface boron box furnace COATED MOLYBDENUM ALLOY coating A(G coating F coating supplier coating surface coating to protect coatings applied coatings tested cracks cristobalite Cross section cyclic tests cyclic-exposure oxidation tests cyclically exposed detected edge conditions Edge Edge Edge edge failures edge preparation examined exposure at 2,500 F in air F specimens failure mechanism Figure gain weight grain structure indicated Langley Research Center Mo-0.5Ti sheet Mo^Si molybdenum-alloy sheet MoSi2 NASA OA number of cycles oxidation-resistant coatings oxygen percent percent percent polarized light probing protect the substrate required to sustain Rummler sheared edges sheared-edge specimens silicide silicide-base silicon carbide specimens tested specimens with coating Stein sustain weight loss test temperature thermally cycled thermocouple tion tumbled edges tumbled-edge specimens typical U.S. Air Force various coatings vertical tube weight change weight gain weight-loss rate X-ray diffraction yield stress Young's modulus zircon boat