NASA NTRS · 19720024128
A graphite-lined regeneratively cooled thrust chamber
Abstract
Design concepts, based on use of graphite as a thermal barrier for regeneratively cooled FLOX-methane thrust chambers, have been screened and concepts selected for detailed thermodynamic, stress, and fabrication analyses. A single design employing AGCarb-101, a fibrous graphite composite material, for a thermal barrier liner and an electroformed nickel structure with integral coolant passages was selected for fabrication and testing. The fabrication processes and the test results are described and illustrated.
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Stubbs, V. R.. 1972-01-01. A graphite-lined regeneratively cooled thrust chamber. https://ntrs.nasa.gov/citations/19720024128
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