Abstract
To study mechanism of cooling high temperature supersonic jet by water injection, the numerical simulation and experiments were carried out. Gas-liquid two phase flow field was calculated by Mixture multiphase model. Vaporization mechanism of water was simulated by coupling equation of water vaporization. The phenomena were photographed by high-speed photography and infrared thermograph. Several temperature monitor points were sensed by thermocouples on the bottom plate. The temperature contours calculated agree well with experimental results in flow structure and temperature distribution. The availability of Mixture multiple model is proved. It can be concluded that the weakened thermal impact and ablation effect accompanying the temperature of head face can be decreased by water injection.
| Original language | English |
|---|---|
| Pages (from-to) | 249-252 |
| Number of pages | 4 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 33 |
| Issue number | 2 |
| Publication status | Published - Apr 2012 |
Keywords
- Cooling effect
- Rocket motor exhaust
- Thermal ablation
- Water injection