压气机叶片前缘分离流动  

AN EXPERIMENTAL INVESTIGATION OF THE FLOW ON LEADING EDGE OF COMPRESSOR BLADE

作　　者：刘火星 蒋浩康 陈懋章 

机构地区：[1]北航气动热力重点实验室,北京100083

出　　处：《工程热物理学报》2004年第6期936-939,共4页Journal of Engineering Thermophysics

基　　金：国家973项目资助(No.G1999022305);国家自然科学基金项目资助(No.59976003;No.50206002);航空基础科学基金项目资助(No.01C51030)

摘　　要：用实验方法研究了压气机叶片前缘分离流动结构。实验是在低速叶栅风洞中完成的。考察了分别具有圆形和椭圆形前缘的NACA65叶型和CDA叶型前缘附近的流动情况。给出了细致的叶片前缘和分离区内的压力分布情况以及叶片前缘附近流动结构。This paper presents an experimental study of the influence of 2d leading-edge geometry on behavior of separation bubbles. The measurements on a nose of enlarged blade were conducted on a special large-scale experimental facility, the pressure distribution and flowfield of flow were measured. The test model used in this study consists of circular leading edge and elliptic leading edge. Results are presented for a range of incidence. The measurement result indicated that the leading edge shape has a large influence on flow details, separation and transition as well as the boundary layer properties after reattached point. The wedge angle appears to be an important role in leading edge geometry parameters.

关 键 词：压气机 分离泡 转捩 前缘 

分 类 号：O357.5[理学—流体力学]