| 尾喷管构型对多循环两相脉冲爆轰发动机流场及性能影响 |
| |
| 引用本文： | 王研艳,翁春生. 尾喷管构型对多循环两相脉冲爆轰发动机流场及性能影响[J]. 航空动力学报, 2013, 28(10): 2256-2266 |
| |
| 作者姓名： | 王研艳 翁春生 |
| |
| 作者单位： | 南京理工大学 瞬态物理国家重点实验室, 南京 210094 |
| |
| 基金项目： | 中央高校基本科研业务费专项资金(30920130112007);预研基金(9140c300202120c30) |
| |
| 摘 要： | 为了研究尾喷管构型对多循环工况下非定常气液两相脉冲爆轰发动机推进性能的影响,运用适应能力强的非结构网格CE/SE(时空守恒元和求解元)方法数值研究了带尾喷管脉冲爆轰发动机的内外流场.结果表明:尾喷管对脉冲爆轰发动机性能的影响在单次循环和多循环工况下有显著差异;当燃料填充率为1、环境压力为0.1MPa时,完成一个周期各种构型尾喷管产生的平均推力由大到小依次为拉伐尔喷管、塞式收敛扩张喷管、收敛喷管、无喷管、直喷管;研究中塞式收敛扩张喷管可以提供最大的冲量和燃料比冲,但完成单个循环的周期最长.
|
| 关 键 词： | 两相爆轰 多循环 CE/SE方法 非结构网格 塞式收敛扩张喷管 推进性能 |
| 收稿时间： | 2013-03-16 |
Effects of nozzle on flow field and performance of multi-cycle two-phase pulse detonation engines |
| |
| WANG Yan-yan and WENG Chun-sheng. Effects of nozzle on flow field and performance of multi-cycle two-phase pulse detonation engines[J]. Journal of Aerospace Power, 2013, 28(10): 2256-2266 |
| |
| Authors: | WANG Yan-yan and WENG Chun-sheng |
| |
| Affiliation: | National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, China |
| |
| Abstract: | The CE/SE(conservation element/solution element) method using adaptable unstructured meshes was derived and applied to calculate the inner and outer flow fields of multi-cycle two-phase pulse detonation engines(PDEs) with different types of nozzles.It was found that the propulsive performance of multi-cycle PDEs with nozzles differed a lot from that of one-cycle PDEs with nozzles.The Laval nozzle offered the highest average thrust in a cycle, while the plug-in-convergent-divergent nozzle provided the maximum impulse and fuel-specific impulse in the longest operation cycle when the nozzles were filled with fuel and the ambient pressure was 0.1MPa. |
| |
| Keywords: | two-phase detonation multi-cycle CE/SE method unstructured mesh plug-in-convergent-divergent nozzle propulsive performance |
|
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
|
点击此处可从《航空动力学报》下载全文 |
