离心压缩机进口导叶/叶轮动静相干的数值研究

周莉; 席光; 蔡元虎

离心压缩机进口导叶/叶轮动静相干的数值研究

1.
西北工业大学动力与能源学院, 西安 710072
2.
西安交通大学能源与动力工程学院, 西安 710049

基金项目: 国家自然科学基金资助(50576073);西北工业大学青年科技创新基金

计量
- 文章访问数: 1606
- HTML浏览量: 89
- PDF量: 484
- 被引次数: 0
出版历程
- 收稿日期: 2006-09-17
- 修回日期: 2006-12-20
- 刊出日期: 2007-10-28

Numerical investigation on IGV/impeller interaction in a centrifugal compressor stage

1.
School of Power and Energy, Northwestern Polytechnical University, Xi' an 710072, China
2.
School of Energy and Power Engineering, Xi'an Jiaotong Univer sity,Xi'an 710049, China

摘要

摘要: 对不同预旋角度下进口导叶/叶轮的相干进行了非定常的数值模拟,讨论了动静相干效应的主要因素,分析了非定常效应对叶轮内流场结构的影响.结果表明,在较大的负预旋角度下,叶轮流动呈现出周期性;造成叶轮内非定常性的主要因素是上游进口导叶的尾迹区,尤其是大尺度分离涡团导致叶轮的进口流动不稳定.导叶尾流的影响只涉及到叶轮通道的一部分(约30%叶片长度),而叶轮的势影响范围从进口导叶尾缘到约20%左右叶片弧长处.叶轮叶片通过频率和叶片旋转频率同时影响着进口导叶内部的非定常流动.
- 航空、航天推进系统 /
- 预旋角度 /
- 动静相干 /
- 尾流 /
- 叶片通过频率 /
- 叶片旋转频率
Abstract: Numerical simulations on the unsteady inlet guide vane(IGV)-impeller interaction were performed under different prewhirl angles.The main factors to IGV-impeller interaction were also discussed to analyze the influence of unsteady flow effect upon flow field of impeller.The results show that the impeller flows periodically under large negative prewhirl angle.In such case, the wake of IGV outlet, especially the large size vortice formed behind IGV, was the key factor to strong unsteady flow in the downstream impeller inlet.The unsteady influence of IGV wake involved only a part of impeller passage(about 30 percent of the blade chord), and the potential repercussion of the impeller ranged from IGV trail edge to 20 percent of the chord.Both the passing frequency and rotating frequency of the blade have influence on the unsteady flow in IGV.
- aerospace propulsion system /
- prewhirl angle /
- IGV-impeller interaction /
- wake /
- passing frequency of the blade /
- rotating frequency of the blade

HTML

参考文献(7)

[1]	Whitfield A,Abdullah A H.Performance of a centrifugal compressor with high inlet prewhirl[J].ASME Journal of Turbomachinery,1998,120(2):487-493.
[2]	Rodgers C.Centrifugal compressor inlet guide vanes for increased surge margin[R].ASME paper,90-GT-158.
[3]	Shu C W,Osher S.Efficient implementation of essentially non-oscillatory shock-capturing schemes[J].Journal of Computational Physics,1989,83(l):32-87.
[4]	席光,周莉,王尚锦.离心压气机进口导叶尾涡非定常发展的数值研究[J].工程热物理学报,2003,24(6):958-960.XI Guang,ZHOU Li,WANG Shangjin.Numerical analysis of the unsteady confined wakes behind the inlet guide vanes of centrifugal compressors[J].Journal of Engineering Thermophysics,2003,24(6):958-960.
[5]	Manwaring S R.Rotor blade unsteady aerodynamic gust response to inlet guide vane wakes[J].Journal of Turbomachinery,1997,115(1):197-206.
[6]	Michael M C.Effect of suction elbow and inlet guide vanes on flow field in a centrifugal compressor stage[R].ASME Paper,GT-2002-30376.
[7]	Michael M C.Unsteady flow around suction elbow and inlet guide vanes in a centrifugal compressor[R].ASME Paper,GT-2004-53273.