轴流压气机转子性能及间隙流动研究  

On Detailed Structure of Tip Clearance Flow in an Isolated Axial Flow Compressor Rotor and Its Effect on Compressor Performance

作　　者：吴艳辉[1] 楚武利[1] 刘志伟[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2005年第6期737-741,共5页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(50506026);中国博士后科学基金(2005037790);西工大青年科技创新基金(M016211)

摘　　要：以一轴流压气机孤立转子实验台为研究对象,对其内部流动进行了全三维的数值模拟。数值计算结果与实验测量结果对比分析表明,程序很好地预测出了孤立转子的总性能和基元性能。以此为基础进一步数值研究了间隙大小的变化对该实验台间隙流动的影响。结果表明,间隙的大小对动叶顶部区域的流动特性,包括间隙流动的发展形式、泄漏涡的强度、间隙流动造成的损失分布等,产生了很大的影响。Experiments up to now cannot reveal completely the structure of tip clearance flow. Our aim is to study theoretically this detailed structure and its important effect on performance of an isolated axial flow compressor rotor. Experimental and numerical investigations were carried out. We used well-known theoretical methods and numerical simulation to study the above-mentioned detailed structure. At NPU Department of Aeroengines we have engaged in aeroengine research, both theoretical and experimental, for many years; so we need not say anything about our normal experimental procedure in this paper other than stating that we have done considerable contract experimental research for Roll-Royce plc. We arranged our experimental setup in such a way as to make it an isolated axial compressor rotor. For such rotor, the calculated results were compared with experimental data and good agreement was achieved between predicted and experimental values all along the spanwise direction of the rotor blade except in the neighborhood of the casing, where it was almost impossible to make measurements experimentally. Near the casing the theoretically calculated total pressure changes very rapidly. Such abrupt change affects very much the performance of axial-compressor rotor.

关 键 词：轴流压气机 数值模拟 性能分析 间隙流 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]