Numerical Simulation of Composite Cooling of RBCC Ejector Rocket Using Gradient Micro-channels

Ejector rocket is an important part of rocket - based combined cycle (RBCC) engine, which provides large thrust for RBCC engine while carrying a high thermal load. In this paper, the composite cooling structure of rocket thrust chamber is designed. The rocket throat is cooled by means of combination of regeneration and liquid film cooling. The width of regeneration cooling passage is gradually distributed from micro scale to small scale in the convergence and expansion sections. The coupled heat transfer characteristics of the composite cooling structure were studied by numerical simulation. The results show that the design of the micro-channel with gradual change can strengthen the throat heat transfer, the liquid film cooling can greatly reduce the inlet and downstream heat flux density, and effectively control the wall temperature.