Gradient Interphase, 3-D Fiber Architecture CMC's, Phase I

A clear need exists for the next generation of Ceramic Matrix Composites (CMC) for Thermal Protection Systems (TPS), propulsion hardware, and other high temperature applications. No "off-the-shelf" materials and/or processes capable of meeting NASA's goals are available, yet completely integrating a unique combination of commercially available or nearly commercially available technologies can meet NASA's goals. The basic elements of the proposed approach focus on refining 3-D fiber architectures, instituting semi-conductor industry controls on the CVI process, forming a gradient interphase between the matrix and fibers, and relying on molecular level modeling results to predict thermal stability. Both 3-D woven and 3-D braided preforms will be designed and manufactured to control the resultant pocket size and shapes to reduce voids during infiltration. Pulsed CVI with an improved out-gas control system will both form a gradient interphase that reduces the CTE mismatch induced internal loads between fiber and matrix and provide a more perfect microstructure while improving processing speed. CMC test articles will be compared to previous work on molecular level thermal modeling for Phase I. Phase II will deliver optimized design and manufacturing processes capable of making impact tolerant, long fatigue life, high temperature CMC's.

Target markets would be: - Gas Turbine Engine Components ? Medium to large market with some R&D money available, though less R&D money than the TPS structures. Performance is a driver, so a premium would be paid for additional performance. Main components where 3TEX should offer advantage are guide vanes for all engines and exhaust flaps for those with afterburners. - Chemical processing (pump components, stirrers, heaters) ? Medium to large market, with some premium available for corrosion resistance. - Industrial burners ? Large market, though very competitive on price and little to no R&D money available. Target NASA markets would be: - TPS structures for next generation Shuttle, Mars and Lunar mission modules, heat shields. Leading edges for hypersonic SSTO vehicles - Propulsion system components, such as nozzles, pump covers, pump components, - Acreage for external combustion engine designs.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.