Abstract
Secondary combustion was experimentally investigated to improve the thrust of rocket ejector mode of RBCC, and to find the influence of thermal choke on thrust. Rocket ejector with strut characteristic was adopted. Multi primary nozzle was used to enhance mixing and atomized-spray injector was used to obtain better spray. Mass flow rate of added fuel, injecting location and physical throat area on rocket ejector performance were investigated. The experimental results show that with the proper mass flow rate and injecting position of secondary fuel thrust augmentation can be obtained under static condition.
| Original language | English |
|---|---|
| Pages (from-to) | 75-77 |
| Number of pages | 3 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 25 |
| Issue number | 1 |
| State | Published - Feb 2004 |
Keywords
- Afterburning
- Fuel control
- Nozzle
- Rocket ejector
- Thrust