Experiments and numerical simulation of active cooling ceramic matrix composite

One challenge of hypersonic airbreathing propulsion system is flow rate matching of fule and coolant. The new cooling strategy, that refractory composite and active cooling are combined, is required in the future. An active cooling composite structure using ceramic matrix composite (CMC) which unite excellences of active cooling and CMC was advanced. To evaluate cooling capability of composite structure, an active cooling composite panel using C/SiC was designed, and experimented with a gas generator that supplied hot gas of high-temperature and high heat transfer rate. The active cooling composite panel was experimented with 3100K gas for 8.5s. A one dimension transient heat transfer model of active cooling composite structure, which could simulate the temperature of multi-layer structure constituted by different materials, was established. Transient temperature of composite structure with different wall materials was calculated. The investigation results show that the active cooling composite structure with C/SiC is available for high-temperature condition in hypersonic airbreathing propulsion system with small quantity of coolant.