Abstract
Challenges of hypersonic airbreathing propulsion system are thermal protection, and, moreover, flow rate matching between fuel and coolant. Compare to conventional material, ceramic matrix composite structure was evaluated for the development of lightweight, active cooling composite panels for ramjet propulsion applications. Subscale active cooling and passive cooling refractory composite panel were designed, and experimented with an experimental facility that supplied lower heat transfer rate and an improved gas generator, which supplied hot gas of high-temperature and high heat transfer rate. The active cooling composite panel was tested with maximum surface temperature over 2000K for a cumulative time of 30s and with maximum surface temperature sustained over 3000K for 9.3s durations. A 1D transient heat transfer numerical simulation was carried out, and multi-layers structure with different materials was modeled. The result showed that the active cooling composite structure was available for high-temperature condition in hypersonic airbreathing propulsion.
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