二维扩压叶栅非定常涡面分析

周晓勃; 侯安平; 周盛

二维扩压叶栅非定常涡面分析

北京航空航天大学航空发动机气动热力重点实验室, 北京 100191

基金项目: 国家自然科学基金(10477002)

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出版历程
- 收稿日期: 2007-07-27
- 修回日期: 2007-10-17
- 刊出日期: 2008-08-28

Analysis of unsteady vortex sheet in2-D axial compressor

National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 轴流压气机内流动是典型的非定常旋涡流动,而现有压气机分析设计体系在定常假设下以流场空间结构为对象.研究压气机内真实流动的途径之一是分析流场时空结构.把转/静叶片交错排列简化为单叶片排,再简化成2-D扩压叶栅.从叶栅非定常涡面的角度来描述非定常旋涡流场时空结构.作为举例,利用合成射流控制涡面演化,改善流场时空结构.此涡面简化模型可为进一步研究叶轮机叶排间干扰复杂流场的时空结构提供分析工具.
- 轴流压气机 /
- 非定常旋涡流动 /
- 涡面 /
- 流场时空结构
Abstract: The flowfield in turbomachinery is characterized by unsteady vortex flow.Contradictorily,the current analysis and design system of axial compressor is based on the spatial structure of the flowfield under the assumption of steady flow.It is understood that one of the methods to investigate the real flow inside the axial compressor is to analyze the temporal-spatial structure of the flowfield.In this paper,an axial compressor stage embedding interlaced rotor and stator rows was simplified into a single blade row,and then further into a 2-Dcompressor cascade.In this way,the temporal-spatial structure of the unsteady vortex flowfield could be described from the angle of unsteady vortex sheet of the cascade.For illustration,the temporal-spatial structure of the flowfield in cascade was transformed through controlling the evolution of vortex sheet by synthetic jet normal to the suction surface of the cascade.The presented unsteady vortex sheet model could be used as an analysis tool for further research on the temporal-spatial structure of stator/rotor interaction in multistage turbomachinery flowfield.
- axial compressor /
- unsteady vortex flow /
- vortex sheet /
- temporal-spatial structure of flowfield

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参考文献(13)

[1]	张涵信.分离流与旋涡运动的结构分析[M].北京:国防工业出版社,2005:2-4.ZHANG Hanxin.Structural analysis of separated flows and vortex motion[M].Beijing:National Defence Industry Press,2005:2-4.(in Chinese)
[2]	Wu J Z,Lu X Y,Denny A G,et al.Post-stall flow control on an airfoil by local unsteady forcing[J].J.Fluid Mech.,1998,371:21-58.
[3]	Gursul I.Review of unsteady vortex flows over slender delta wings[J].Journal of Aircraft,2005,42 (2):299-319.
[4]	Zhou S,Zheng X Q,Hou A P,et al.J.Interaction of unsteady separated flow over multi-bodies moving relatively in the same flow field[J].Journal of Sound and Vibration,2005,288,Issues 4-5:981-1009.
[5]	Johnson I A,Bullock R O.Aerodynamic design of axial flow compressors[R].NASA SP-36,1965.
[6]	Adamezyk J J.Aerodynamic of multistage turbomachinery flow in support of aerodynamic design[R].ASME 99-GT-80,1999.
[7]	普朗特 L,奥斯瓦提奇 K,维格哈特K著.流体力学概论[M].郭永怀,陆士嘉,译.北京:科学出版社,1981.Prandtl L,Oswatitseh K,Wieghardt K.Brief introduction to fluid mechanics[M].Translated by GUO Yonghuai,LU Shijia.Beijing:Science Press,1981.(in Chinese)
[8]	吴介之,马晖扬,周明德.涡动力学引论[M].北京:高等教育出版社,1993:494-511.WU Jiezhi,MA Huiyang,ZHOU Mingde.Introduction to vorticity and vortex dynamics[M].Beijing:Higher Education Press,1993:494-511.(in Chinese)
[9]	童秉纲,张炳暄,崔尔杰.非定常流与涡运动[M].北京:国防工业出版社,1993:131-141.TONG Binggang,ZHANG Bingxuan,CUI Erjie.Unsteady flows and vortex motion[M].Beijing:National Defence Industry Press,1993; 131-141.(in Chinese)
[10]	Mokry M.Numerical simulation of aircraft trailing vortices interacting with ambient shear or ground[J].Journal of Aircraft,July-Aug.2001,38:636-643.
[11]	Shen M Y,Niu X L,Zhang Z B.The three-point fifth-order accurate generalized compact scheme and its applications[J].Acta Mechanics Sinica,2001,17(2):142-150.
[12]	Lele S K.Compact finite difference schemes with spectrallike resolution[J].Journal of Computational Physics,1992,103:16-42.
[13]	侯安平.叶轮机非定常流动研究方法的初步探索[R].北京:北京航宅航天大学博士后研究工作报告,2005:14-20.HOU Anping.Exploration on method of studying unsteady flow in turbomachinery[R].Beijing:A Report Presented to Beihang University for Finishing of Post Dr.,2005:14-20.(in Chinese)