Enhanced Oxidation Resistant Graded C-Carbide CMC Via Rapid CVI Process

Increased space launch payload requirements are driving the need for liquid rocket engines with higher thrust levels, specific impulses and thrust-to-weight ratios. This has triggered significant development efforts in improving the capabilities and reducing the costs of C/C composite nozzle extensions.In contrast to a paper study, this Phase 1 proposal will demonstrate the cost advantages of a rapid CVI process for producing a higher temperature, more durable C/C based 3D woven composite.Thermal-mechanical property test results will be combined with microstructural and compositional analyses to optimize and compare the rapid CVI method versus a conventional isothermal CVI process. The Phase 1 will also produce a manufacturing cost analysis of the GP-RTG CVI process in addition to outlining the data base requirements and the sequence of coupon, sub-element, and component tests needed to establish the basis for nozzle extension design, processing, and inspection.