Abstract
The experimental investigations on PDRE key issues of two-phase detonation initiation, reliable and controllable operation, deflagration to detonation transition mechanism, detonable range, thrust measurements and augmentation with nozzles were presented in detail on PDRE test models using kerosene as fuel and oxygen as oxidizer. The results show that this PDRE prototype can reliably and controllably be operated with high frequency and its performance is good. All 3 chosen nozzles can augment PDRE performance and maximal augmentation of 18% was attained by the convergent nozzle.
| Original language | English |
|---|---|
| Pages (from-to) | 385-389 |
| Number of pages | 5 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 27 |
| Issue number | 5 |
| State | Published - Oct 2006 |
Keywords
- Initiation
- Nozzle augmentation
- Performance testing
- Pulse detonation rocket engines
- Two-phase effect