STRUCTURE DESIGN AND PERFORMANCE TEST OF A HIGH TEMPERATURE RISE COMBUSTOR BASED ON COMBUSTION-GAS WIND TUNNEL DEVICE

The convection heating method of high temperature combustion-gas generated by the gas-heating wind tunnel is used as a popular test method for performance assessment of thermal protection systems (TPS) of hypersonic vehicles. In this paper, a combustion-gas wind tunnel device based on two-stage atomization, two-stage combustion/mixing mode of high-temperature rise combustor (ACWT-TATCM) is designed. In the performance test under normal atmospheric temperature and atmospheric pressure, the continuous, accurate, rapid, and ultra-wide linear adjustment of the combustion-gas temperature can be achieved by adjusting the mass flow of aviation kerosene while keeping the total air supply unchanged. The results show that the combustion-gas temperature can rise from 300 K to 2100 K within 3 s. In addition, when the air mass flow is 100 g/s, the ACWT-TATCM can reach the optimal operation state. The combustion efficiency can be up to 97.55%, while the optimal values of outlet temperature distribution coefficient and total pressure recovery coefficient are 0.209 and 97.3%, respectively.