| 两类涡轮激波结构及演化规律研究 |
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| 引用本文： | 季路成,马伟涛,冯福金.两类涡轮激波结构及演化规律研究[J].北京理工大学学报,2015,35(6):571-575. |
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| 作者姓名： | 季路成 马伟涛 冯福金 |
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| 作者单位： | 北京理工大学宇航学院,北京,100081;北京理工大学宇航学院,北京,100081;北京理工大学宇航学院,北京,100081 |
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| 基金项目： | 国家自然科学基金资助项目(51376023) |
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| 摘 要： | 针对收缩、收缩-扩张两类涡轮叶栅中激波结构及其演化规律的问题,采用数值模拟的方法研究得到了两类叶栅在变工况下的流场等马赫数云图及叶表马赫数分布,经分析获得了关于收缩、收缩-扩张叶栅在超跨音工况下激波结构主要差别的认识及激波附面层分离的基本判别准则,即激波前后压比达到1.4时附面层将发生分离.
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| 关 键 词： | 超跨音涡轮 激波结构 激波附面层干扰 数值模拟 |
| 收稿时间： | 2013/11/20 0:00:00 |
Research on the Shock Wave Structure and Its Evolution in Turbine Cascades |
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| JI Lu-cheng,MA Wei-tao and FENG Fu-jin.Research on the Shock Wave Structure and Its Evolution in Turbine Cascades[J].Journal of Beijing Institute of Technology(Natural Science Edition),2015,35(6):571-575. |
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| Authors: | JI Lu-cheng MA Wei-tao and FENG Fu-jin |
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| Institution: | School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China |
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| Abstract: | To clarify the shock wave structure and its evolution of turbine cascades working in two different conditions, constrictive and contrictive-expandable, the blade surface Mach number distribution and Mach contours were obtained with numerical simulation. With the simulation result analysis, the law of shock wave evolution, and the main difference between the shock wave structures of constrictive and contrictive-expandable turbine cascades in transonic working conditions were obtained. The separation standard of the boundary layer behind the shock wave was also obtained. When the pressure ratio of post and pre the shock wave reaches 1.4, the boundary layer will separate. |
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| Keywords: | transonic turbine shock wave structure interaction between shock wave and boundary layer numerical simulation |
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