Rocket nozzle material
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United States of America Patent
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Issued Date -
Jul 6, 2006
app pub date -
Jan 6, 2005
filing date -
Jan 6, 2005
priority date (Note) -
Abandoned
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Abstract
An aluminum burning rocket engine lining. The lining material is or includes one or more transition metal carbides of tantalum, niobium or vanadium. Applicants have determined that in aluminum burning rocket engines molten Al.sub.2O.sub.3 coats the inside surface of the throat of the rocket nozzle protecting certain transition metal carbides from oxidizing reactions at temperatures below a specific temperature that Applicants call the reaction initiated temperature (RIT). Applicants have proven through calculations and tests that a variety of transition metal carbide compositions as good as or better than tungsten as an engine liner material for aluminum burning rocket engines.
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