Abstract
The 3D reaction flow field in the afterburning chamber of solid ducted rocket motor with binary dual-underside inlet mode was numerically simulated by means of RNG k-ε turbulence model and one step eddy-dissipation combustion model. Change trend of combustion efficiency in afterburning chamber was obtained. The influence of afterburning chamber length on secondary combustion efficiency and flow field were analyzed based on direct-connected ground simulation test. The results show that the efficiency of secondary combustion can be improved obviously with increase of afterburning chamber length, but there exists a suitable design value; when the afterburning chamber length is more than the design value, combustion efficiency is improved a little.
| Original language | English |
|---|---|
| Pages (from-to) | 292-294+298 |
| Journal | Guti Huojian Jishu/Journal of Solid Rocket Technology |
| Volume | 30 |
| Issue number | 4 |
| State | Published - Aug 2007 |
Keywords
- Afterburning chamber length
- Numerical simulation
- Secondary combustion
- Solid ducted rocket motor