压气机中尾迹/边界层作用模型的分析与验证  

Analysis and verification of wake/boundary layer interaction model in compressor

作　　者：杨荣菲[1] 李志平[1] 李秋实[1] 周盛[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191

出　　处：《航空动力学报》2011年第7期1647-1653,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(10902008);"凡舟"青年科研基金(20090401)

摘　　要：基于叶轮机中尾迹的负射流效应,考虑了边界层外缘黏性力项对边界层发展的影响,推导了尾迹/边界层相互作用的数学模型,并建立了边界层动量厚度与压气机叶片负荷变化的定量关系,对模型进行了数值模拟和实验验证.结果表明:①此模型能够较好地预测尾迹通过频率对压气机负荷的影响,压气机压升随着尾迹通过频率的变化存在极大值;②尾迹引起边界层当地压力梯度变化,是影响压气机负荷的主要因素.A wake/boundary layer interaction model was derived based on negative jet effect of wake transport in turbomachinery, in consideration of the influences of outer boundary layer＇s viscous force on boundary layer development. Then, the relationship between pressure rise and momentum thickness was established. An experiment was designed to verify this model about effect of wake passing frequency on compressor pressure rise at fixed wake depth and wake width. Comparison of model and experimental results indicates that： （1） The model can be used to predict the effect of wake passing frequency on compressor pressure rise effectively. （2） The key factor of wake/boundary layer interaction is local pressure gradient that changes with wake, which leads to pressure rise finally.

关 键 词：负射流 边界层动量厚度 尾迹/边界层作用 尾迹通过频率 压气机 

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]