来流条件对叶片表面附面层影响的实验研究  

Experiment Investigation of Boundary Layer on Cascade Surface under Different Inlet Flow Conditions

作　　者：薄相峰[1] 刘波[1] 项效镕[1] 王庆伟[1] 曹志远[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072

出　　处：《航空工程进展》2011年第1期93-99,共7页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金项目(50976093)

摘　　要：本文突破传统的附面层总压测量方法,采用附面层总压探针实现测量平面叶栅叶片表面真实的附面层内总压,实验过程中改变来流马赫数测量叶片吸力面及压力面附面层内总压,并通过相关计算获得附面层厚度的一系列参数。实验目的在于研究来流条件对平面叶栅叶片表面附面层的影响。实验结果表明:与来流马赫数相比来流攻角对附面层厚度影响较大,不同攻角下叶片吸力面、压力面的附面层位移厚度、动量厚度等参数呈现出一定的变化规律;马赫数的变化对附面层厚度的影响幅度较小,从整体来看随着马赫数的增加附面层厚度略有下降。In this paper,the measure method is different from traditional method.Using the total pressure probe,the real total pressures in the boundary layer of cascade blade surface are measured.The flow Mach number is changed in the experiment.Some parameters about the boundary thickness are calculated.The purpose of the experiment is to examine the influence of the inlet flow conditions on the boundary layer of cascade blade surface.The experiment results indicate that the influence of the incidence on the boundary layer is greater than the inlet Mach.The parameters about the boundary thickness have some different regulations under different inlet flow condition.The effect of flow Mach on the boundary thickness is small.The boundary thickness is downtrend with the increase of the Mach.

关 键 词：压气机 来流条件 附面层 平面叶栅 

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]