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| 跨声速轴流压气机间隙泄漏流触发旋转失速 | |
| 引用本文： | 胡书珍,张燕峰,卢新根,张宏武,朱俊强.跨声速轴流压气机间隙泄漏流触发旋转失速[J].推进技术,2010,31(1):47-51. |
| 作者姓名： | 胡书珍 张燕峰 卢新根 张宏武 朱俊强 |
| 作者单位： | 1. 中国科学院,工程热物理所,北京,100190;中国科学院研究生院,北京,100190 2. 西北工业大学,动力与能源学院,陕西,西安,710072 3. 中国科学院,工程热物理所,北京,100190 |
| 基金项目： | 国家自然科学基金青年科学基金(50806073) |
| 摘 要： | 通过对跨声速轴流压气机NASA转子37进行单通道定常及多通道定常、非定常数值模拟,单通道定常数值模拟结果与实验结果能较好吻合。多通道非定常数值模拟结果显示,间隙泄漏流及其与激波干涉的非定常振荡,触发突尖型旋转失速先兆,具体表现为叶顶前缘间隙泄漏流溢出。失速团首先在叶顶处形成,且速度约为80%转速。随着流量的下降,失速团进一步发展,在失速通道内,激波与叶片前缘完全分离,且在叶片尾缘出现回流。当转子完全数值失速时,失速团周向尺度约为4个通道,且径向占据约半个叶高。 |
| 关 键 词： | 跨音速压气机 转子 失速 泄漏 数值仿真 |
Tip leakage flow trigger rotating stall in a transonic axial-flow compressor |
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| Hu Shuzhen,Zhang Yanfeng,LuXin-gen,Zhang Hongwu and ZhuJunqiang.Tip leakage flow trigger rotating stall in a transonic axial-flow compressor[J].Journal of Propulsion Technology,2010,31(1):47-51. | |
| Authors: | Hu Shuzhen Zhang Yanfeng LuXin-gen Zhang Hongwu and ZhuJunqiang |
| Institution: | HU Shu-zhen1,2,ZHANG Yan-feng3,LU Xin-gen1,ZHANG Hong-wu1,ZHU Jun-qiang1(1.Inst.of Engineering Thermophysics,Academia Sinica,Beijing 100190,China,2.Graduate School of the Chinese Academy of Sciences,3.School of Power , Energy,Northwestern Polytechnical Univ.Xi\'an 710072,China) |
| Abstract: | The single-passage steady and multi-passages steady/unsteady numerical simulation of the transonic axial-flow compressor-NASA Rotor 37 were investigated.The numerical results agreed well with experimental test data with estimation of the global performance.For the multi-passages unsteady computation,detailed analysis of the internal flow field with the NASA Rotor 37 led to some preliminary conclusion for unsteady behavior of the tip leakage flow,the interaction of the vortex and the shock wave and trigger s... |
| Keywords: | Transonic compressor Rotor Stalling Leakage Numerical simulation |
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