Rapid Fabrication of SiCf/SiC composite via Field Assisted Sintering Technique for Turbine Applications Navy SBIR FY2013.1 Sol No.: Navy SBIR FY2013.1 Topic No.: N131-072 Topic Title: Rapid Fabrication of SiCf/SiC composite via Field Assisted Sintering Technique for Turbine Applications Proposal No.: N131-072-0014 Firm: SCIENCETOMORROW, LLC 1229 Garrisonville Rd Ste 201 Stafford, Virginia 22556 Contact: Subhadarshi Nayak Phone: (703) 880-6622 Web Site: www.scienceTomorrow.biz Abstract: State-of-the-art manufacturing cost for SiC matrix composites CMC components is still very high due to long lead times despite of many research efforts. ScienceTomorrow, in collaboration with Applied Research Lab of Penn State University and its OEM partners, will investigate ceramic fiber-reinforced ceramic matrix composite fabrication via a novel field assisted sintering technique. Under the concurrent application of high pulsed current density, pressure and temperature the green structure will be consolidated. Processing-microstructure-properties relationships will be established first empirically during the Base Period and numerically in the option period to allow complete exploitation of the benefits of the novel processing approaches. The research will utilize multi-scale material characterization and integrated multi-scale multi-physics computational modeling for developing processing-properties-structure correlation. The success criteria are set in comparison to current fabrication methods: (a) Chemical Vapor Infiltration, (b) Melt Infiltration, and (c) Polymer Impregnation Pyrolysis. ScienceTomorrow will collaborate with an OEM for process optimization and commercialization that will allow the OEM to exploit the benefits of the FAST processing method for SiCf/SiC turbine components. Ultimately, the FAST process will enable the production of more affordable 2700�F capable CMCs. Benefits: Complete exploitation of the benefits of the novel processing approach will result in superior mechanical properties at room temperature and elevated temperatures. Process optimization and commercialization will allow the OEM to exploit the benefits of the FAST processing method for SiC CMC turbine components. Ultimately, the FAST process will enable the production of more affordable 2700�F capable CMCs which could translate to a 2% decrease in fuel or a 2.1% increase in mission range for limited engine parts. The high specific strength high-temperature material will also benefit improving performance of turbine engine components, rocket engine nozzles, air-breathing propulsion flow path structures, hot control surfaces and leading edges applications. It will also provide increased thrust-to-weight ratios, lower emissions and improved specific fuel consumption, engine turbines tasked to operate at temperatures higher than 2200F in order to increase the efficiency and the performance of gas turbine engines as in AETD program. Return