Investigation of the influence of secondary nozzles on the performance of rocket ejectors

The utilization of rocket ejector is important to structural integration of rocket based combine cycle motor, because it may decrease weight and complexity of the motor. Numerical simulation and experimental approaches are adopted to investigate the influence of secondary nozzle on the performance of rocket ejector. Unstructured meshes are used in 3-D numerical simulation. The results indicate that the bypass ratio decreases and the static pressure in integrated ejector combustor increases with the decrease of exit area of secondary nozzle. There is an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.