摘要
在详细研究顶隙泄漏流的结构及其演化的基础上,分析了Rotor 37的失速机理,并对不同深度、宽度和位置的环向沟机匣处理方式进行了比较研究.研究发现:在该研究的顶隙高度下,发生在叶尖尾缘附近的大面积流动分离是造成压气机失速的直接原因.因而布置在叶片中段和尾缘的环向沟有利于提高压气机的喘振裕度.同时还发现,环向沟的深度对于其产生作用并没有明显的影响,而其宽度的影响则较为明显.
Based on the detailed computational fluid dynamics（CFD） study on the structure and development of tip leakage flow in NASA（National Aeronautics and Space Administration） Rotor 37,the stall mechanism was discussed.A study of the circumferential grooves casing treatment with different locations,depth and width was also performed.The simulation reveals that the large separation zone at the trailing edge near the blade tip is directly attributable to the compressor stall at the configuration studied in this paper.As a result,the circumferential grooves at the mid-chord and the trailing edge appear to be effective on the extension of the stall margin.Meanwhile,it is found that the depth of the grooves does not influence obviously its effect,while the width seems to be a more important parameter.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第12期2673-2682,共10页
Journal of Aerospace Power
关键词
跨声速压气机
顶隙泄漏流
失速机理
环向沟机匣处理
几何参数研究
transonic compressor
tip leakage flow
stall mechanism
circumferential grooves casing treatment
geometric parameter study
