摘要
以某型压气机叶型为研究对象,在宽广的攻角范围内研究了叶片表面绊线技术对压气机流动分离的影响。研究结果表明,在正攻角范围内,设置在叶片分离点上游的绊线,使压气机的分离得到有效抑制,当攻角为15°时,压气机的总压损失降低19%;在所研究的负攻角范围内,绊线的引入对流场的影响并不显著。因此合理设计绊线可以在宽广的工况范围内有效降低压气机叶片气动损失。
The influence of blade surface tripping technique on compressor flow separation is investigated in a wide range of attack angles.The results show that the separation of the compressor is effectively suppressed at the positive angle of attack,which is set at the upstream of the blade separation point.When the angle of attack is 15 degrees,the total pressure loss of the compressor is reduced by 19%.In the range of negative angle of attack studied,the effect of trip line on field is not significant.Therefore,a reasonable design of the trip line can effectively reduce the aerodynamic losses of compressor blades in a wide range of operating conditions.
作者
白涛
高山
BAI Tao;GAO Shan(School of Aircraft,Xi’an Aeronautical,Xi’an 710077,China;School of Marine Science and Technology,Northwestern Polytechnic University,Xi’an 710072,China)
出处
《兵器装备工程学报》
CAS
北大核心
2018年第3期157-161,173,共6页
Journal of Ordnance Equipment Engineering
基金
西安航空学院校级科研基金项目(2017KY1230)
关键词
压气机
边界层分离
绊线技术
气动损失
compressor
separation bubble
trip line technology
aerodynamic loss
