NASA NTRS · 19910000320
Iridium/Rhenium Parts For Rocket Engines
Abstract
Oxidation/corrosion of metals at high temperatures primary life-limiting mechanism of parts in rocket engines. Combination of metals greatly increases operating temperature and longevity of these parts. Consists of two transition-element metals - iridium and rhenium - that melt at extremely high temperatures. Maximum operating temperature increased to 2,200 degrees C from 1,400 degrees C. Increases operating lifetimes of small rocket engines by more than factor of 10. Possible to make hotter-operating, longer-lasting components for turbines and other heat engines.
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Schneider, Steven J., Harding, John T., Wooten, John R.. 1991-07-01. Iridium/Rhenium Parts For Rocket Engines. https://ntrs.nasa.gov/citations/19910000320
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