叶型探针对压气机叶栅气动性能影响的试验与数值研究  

Experimental and Numerical Investigation of Airfoil Probe Influences on the Performance of Compressor Cascade

作　　者：向宏辉[1] 任铭林[1] 马宏伟[2] 贺象[2] 王绍川[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703 [2]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《燃气涡轮试验与研究》2010年第4期10-16,共7页Gas Turbine Experiment and Research

基　　金：航空科学基金资助项目(2008ZD24012)

摘　　要：利用平面叶栅风洞,开展了安装叶型探针的压气机叶栅吹风试验。通过测取不同工况下叶片表面压力、栅后尾迹等气动参数,分析了叶栅在安装叶型探针前后的性能变化。同时,采用数值模拟方法,对前缘探头绕流旋涡在叶栅流道内部的发展演变规律及其损失特性进行了探索。研究结果表明:①探针对叶栅局部流场的扰动作用比较明显,其影响特性与叶栅工作状态相互关联;②探针对其所在叶片以及相邻两侧叶片总压损失系数的影响程度随来流攻角发生显著变化;③安装探针后,栅后尾迹与主流掺混作用加强,导致尾迹沿周向存在较为严重的扩散作用;④负攻角条件下,前缘实体探头会诱导叶片出口靠近叶盆表面出现一定强度与尺度的涡系结构。A compressor stator linear cascade with airfoil probe was tested in a supersonic and transonic cascade wind tunnel.The performance changes of the compressor cascade with and without airfoil probes were compared through measuring the blade surface pressure and wake parameters at different operating conditions.Furthermore,the evolution of flow vortex around probe head at the leading edge of blade in the cascade passage and its loss characteristics were investigated by using a three-dimensional numerical simulation method.The results indicate that：（1） The disturbance actions of airfoil probe on the partial flowfield of the compressor cascade are considerably significant,and the impact characteristics are connected with the operating conditions of the cascade;（2） The influence of airfoil probe on the total pressure loss coefficients of the blade installed airfoil probe and its adjacent blades is varied greatly with the attack angles of compressor cascade;（3） After installing airfoil probe at the leading edge of one of the cascade blades,the distribution of cascade wake pressure along circumferential direction will become more non-uniform,and the mixing between the wake regime and the main flow will also enhance,which leading to the existence of cascade wake diffusion along circumferential direction;（4） At the condition of negative attack angle,the solid probe will induce vortex structure at the outlet location of blade pressure surface.

关 键 词：叶型探针 压气机叶栅 等熵马赫数 总压损失系数 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]