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NASA NTRS · 19670053335

Effects of exhausts from aluminized solid propellants on launch facilities.

Darrow, E. A.·Lays, E. J.
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Abstract

Effect on protective coatings of launch pads of exhaust products, chamber pressure, nozzle diameter, etc, from aluminized solid propellant rocket motors

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PROTECTIVE COATINGEXHAUST NOZZLELAUNCHING PADCHAMBER PRESSURESOLID PROPELLANT ROCKET ENGINE

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Darrow, E. A., Lays, E. J.. 1967-07-01. Effects of exhausts from aluminized solid propellants on launch facilities.. https://ntrs.nasa.gov/citations/19670053335

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NASA NTRS1967

Development of Coatings for Tantalum Alloy Nozzle Vanes

A group of silicide coatings developed for the T222 tantalum-base alloy have afforded over 600 hours of protection at 1600 and 2400 F during cyclic exposure in air. These coatings were applied in two steps. A modifier alloy was applied by slurry techniques and was sintered in vacuum prior to siliciding by pack cementation in argon. Application of the modifier alloy by pack cementation was found to be much less effective. The addition of titanium and vanadium to molybdenum and tungsten yielded beneficial modifier alloys, whereas the addition of chromium showed no improvement. After siliciding, the 15Ti- 35W-15V-35Mo modifier alloy exhibited the best performance; one sample survived 1064 hours of oxidation at 2400 F. This same coating was the only coating to reproducibly provide 600 hours of protection at both 1600 and 2400 F; in the second and third of three experiments, involving oxidation of three to five specimens at each temperature in each experiment, no failures were observed in 600 hours of testing. The slurry coatings were also shown to protect the Cb752 and D43 columbium-base alloys.

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