基于冲击冷却的RBCC引射火箭局部热防护数值模拟

Ejector rockets are capable of providing large thrust for rocket-based combined cycle (RBCC) engines, but face extremely high thermal loads at the throat. In this paper, the impingement cooling method is proposed to provide local thermal protection of the ejector rocket. A threedimensional numerical model of jet impingement cooling is established. The effects of throat radius and the number of impingement holes on the cooling performance are studied. The results show that in the range of design radius R=(1∼2)R_t, the value of R has no obvious effect on jet impingement heat transfer. The average convective heat transfer coefficient of the target surface decreases with the increase of the number of impingement holes n, and the distribution uniformity increases first and then decreases with the increase of n. The heat transfer efficiency is the highest when the number of impingement holes n=6.