CHEMICAL CORROSION OF ROCKET LINER MATERIALS AND PROPELLANT PERFORMANCE STUDIES. VOLUME 1
Final technical rept.
PHILCO NEWPORT BEACH CA AERONUTRONIC DIV
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Theoretical equilibria resulting from corrosion of refractory nozzle materials by hot combustion gases were determined for a number of systems. The refractories included graphite, tungsten, TaC, HfN, TiC, ZrC, ZrB2, MgO, and HfO2. The bulk of the corrosion studies were performed for pure species of arbitrary composition, including AlF3, BF2, BF3, BOF, HBO2, BeF2, CO, CO2, HCl, HF, H2, H2O, LiF, N2, and condensed Al2O3 and BeO. Several real propellant systems were investigated. In general, corrosion effects were determined for temperatures in the range 15005000 K, and for a nominal total pressure usually 1000 psia. Tungsten and graphite generally rank the most resistant of the materials considered. Tungsten has an advantage over graphite for combustion systems containing oxygen or hydrogen, while the reverse is true for systems based upon fluorine. Tantalum carbide also is reasonably resistant to attack by many systems. No material considered was capable of withstanding high- temperature attack by severely oxidizing atmospheres, such as CO2 and H2O.
- Solid Propellant Rocket Engines