Numerical investigation on diffusion afterburning of RBCC in ejector mode

Numerical investigation on kerosene-gas fueled diffusion and afterburning (DAB) process of rocket based combined cycle (RBCC) was conducted. The simple fast one-step irreversible chemistry reaction model, 3-D limited volume methodology with non-structured grids, and κ-ε turbulent model were employed in the research. And the result shows that due to induction of second combustion, although the thrust positive augmentation of RBCC system does not appear in static sea-level free ejection status, thrust performance can be improved greatly; it is helpful to achieve high combustion efficiency when the second fuel injector is located at the rear section of the second combustor.