摘要
本文利用高频响动态压力测试技术测量了某跨音压气机转子叶尖间隙流场，其中包括对跨音转子叶尖漏流和激波／漏流干扰的细致流场特征．测试结果表明激波在机匣壁面处受漏流干扰的影响相当大，这一干扰分别来自于前缘漏流涡的干扰和叶尖第二次漏流对通道激波的直接冲击干扰，使激波结构呈“S”形.在低背压高攻角条件下，转子存在十分明显的尾涡．
Flow field in tip clearance of a transonic compressor rotor, which include the detailed investigating of tip clearance leakage flow and its interaction with passage shock wave, is measured in the technique of high frequency response pressure probe. The result shows that the passage shock structure is strongly interacted by the tip clearance leakage flow near the casing of rotor. These are two sources of interaction existing, the first is from the leading edge leakage vortex, and the second is the secondary leakage flow, which impact the shock wave straightly. Under the influence of leakage flow, the structure of passage shock presents a character 'S'. A distinct trail vortex exists under the lower back pressure and high incidence angle condition.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
1998年第5期553-558,共6页
Journal of Engineering Thermophysics
基金
航空科学基金
关键词
压气机
转子
泄漏流
激波结构
叶兴
流场
compressor rotor, leakage flows, shock structure, shock/leakage flow interaction
