| 跨声轴流压气机激波/泄漏涡/边界层分离相互作用的影响 |
| |
| 引用本文： | 谢芳,楚武利,张皓光.跨声轴流压气机激波/泄漏涡/边界层分离相互作用的影响[J].航空动力学报,2012,27(2):425-430. |
| |
| 作者姓名： | 谢芳 楚武利 张皓光 |
| |
| 作者单位： | 1.西北工业大学 动力与能源学院, 西安 710072 |
| |
| 基金项目： | 国家自然科学基金(51006084) |
| |
| 摘 要： | 对跨声速转子Rotor37进行三维定常数值模拟,将设计间隙与零间隙进行对比研究,分析激波、边界层分离、间隙泄漏涡相互作用影响.数值计算显示:激波、泄漏涡、边界层分离相互影响,加速了失速的发生;减小间隙可以起到扩稳的作用.根据边界层分离、间隙泄漏涡在叶栅高度上的影响范围,提出利用抽吸技术进行被动控制改善流道流动状况时抽吸点的设置位置.
|
| 关 键 词： | 跨声速 轴流压气机 激波 间隙泄漏涡 边界层分离 |
| 收稿时间： | 5/9/2011 12:00:00 AM |
| 修稿时间： | 8/2/2011 12:00:00 AM |
Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor |
| |
| XIE Fang,CHU Wu-li and ZHANG Hao-guang.Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor[J].Journal of Aerospace Power,2012,27(2):425-430. |
| |
| Authors: | XIE Fang CHU Wu-li and ZHANG Hao-guang |
| |
| Institution: | 1.School of Power and Energy, Northwestern Polytechnical University, Xi’an 7100722.The 204 Office, Xi’an Institute of High Technology, Xi’an 710025, China |
| |
| Abstract: | Three-dimensional(3-D) numerical simulations were conducted to analyze the flow field in transonic rotors Rotar 37. The results with design tip clearance were compared with no tip clearance condition. Mutual influence of shock, boundary layer separation, clearance leakage the vortex accelerated the occurrence of stalled. Reduce clearance can enlarge the steady border. The suction position applied on passive control technology to improve port flow condition was given. |
| |
| Keywords: | transonic axial compressor shock tip leakage vortex (TLV) boundary layer separation |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 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》下载免费的PDF全文 |
