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三维扩压叶栅非定常流动机理研究的频谱分析
引用本文:吴鸿斌,郑新前,周盛.三维扩压叶栅非定常流动机理研究的频谱分析[J].航空动力学报,2005,20(2):267-272.
作者姓名:吴鸿斌  郑新前  周盛
作者单位:北京航空航天大学,航空发动机气动热力国防科技重点实验室,北京,100083
摘    要:计算了三维直叶栅在不同攻角、不同马赫数下的流动情况,得到流场的非定常解,并进行了频谱分析,对叶栅非定常流动的流场结构和流动机理做了初步的探讨。分析计算结果表明:在来流均匀,定常边界条件下,叶栅内流动仍然表现出强烈的非定常性。分离区和尾迹中的流动,以旋涡的有规律周期性脱落为主要的运动形式。旋涡脱落的频率,随着攻角和马赫数的变化而变化:同马赫数下,攻角越大,频率越低;同攻角下,马赫数越高,频率越高。同时,在同一工况下,旋涡频率沿叶高呈非均匀分布,叶中区域频率相对低,靠近端壁区频率相对高。

关 键 词:航空、航天推进系统  轴流压气机  三维叶栅  非定常流动  分离流  旋涡脱落频率
文章编号:1000-8055(2005)02-0267-06
收稿时间:2004/5/30 0:00:00
修稿时间:2004年5月30日

Frequency Analysis of Three Dimensional Compressor Cascade Unsteady Flow Mechanism Research
WU Hong-bin,ZHENG Xin-qian and ZHOU Sheng.Frequency Analysis of Three Dimensional Compressor Cascade Unsteady Flow Mechanism Research[J].Journal of Aerospace Power,2005,20(2):267-272.
Authors:WU Hong-bin  ZHENG Xin-qian and ZHOU Sheng
Institution:National Key Laboratory of Aircraft Engine,Beijing University of Aeronautics and Astronautics,Beijing100083,China;National Key Laboratory of Aircraft Engine,Beijing University of Aeronautics and Astronautics,Beijing100083,China;National Key Laboratory of Aircraft Engine,Beijing University of Aeronautics and Astronautics,Beijing100083,China
Abstract:A simulation using unsteady Reynolds-averaged viscous turbulent equations was carried out.The results show that the flow in the separation region and wake region is characterized as periodic or quasi-periodic vortex shedding and the frequency of vortex shedding is varied with incidence and Mach number.At same Mach number,the frequency of vortex shedding decreases with the increase of incidence.Yet,the frequency increases with the increase of Mach number keeping incidence unchanged.In the same situation,the frequency of vortex shedding differs along the span of the cascades.The frequency is lower at the middle of the span than that at the hub.
Keywords:aerospace propulsion system  axial flow compressor  3D cascade  unsteady flow  flow separation  frequency of vortex shedding
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