波纹对高亚声叶型性能影响试验与机理分析  

Experiment and mechanism analysis on the effect of waves on the performance of high-subsonic profile

作　　者：杨光 高丽敏[1,2] 王浩浩 黄萍 YANG Guang;GAO Limin;WANG Haohao;HUANG Ping(School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China;The National Key Laboratory of Aerodynamic Design and Rescarch,Northwestern Polytechnical University,Xi'an 710072,China;Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621000,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]西北工业大学翼型、叶栅空气动力学国家级重点实验室,西安710072 [3]中国航发四川燃气涡轮研究院,四川绵阳621000

出　　处：《航空动力学报》2024年第7期229-237,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51790512);国家自然科学基金面上项目(52175436)。

摘　　要：基于压气机叶片加工过程中出现的波纹现象,加工出4种波纹形式叶栅试验件并开展平面叶栅吹风试验,得到波纹对叶型性能及表面负荷的影响规律并进行机理分析.结果表明:叶背波纹现象整体上增加叶型损失.负攻角下,叶背波纹对流场的影响会传播至叶背下游和叶盆,整体改变叶型表面压力分布.气流在波纹出现位置产生"加速-减速"的周期性更迭,波纹宽度直接决定了更迭的频次,不同的波纹初始相位影响叶背前缘区域加速趋势.叶背波纹会改变前缘"吸力峰"强度,波纹对叶型前缘转捩位置的作用机制与叶型自身特性有关,当波纹起始位置在原始叶型转捩位置前,吸力峰强度的变化会改变前缘转捩位置.Based on the appearance of waves in the compressor blade processing,cascades with four kinds of waves were processed,and the plane cascade experiment was carried out,then the influences of aerodynamic performance and pressure distribution were obtained and the mechanism was analyzed.Results showed that the loss of those profiles with waves was overall larger than that of original profile.Under negative attack of angle,the influence of wave spread to the downstream and pressure side and changed the pressure distribution of profile.Moreover,the flow experienced repeated acceleration-deceleration changes on suction side of the blade where waves appeared.The width of the wave directly determined the frequency of acceleration-deceleration changes,and different initial phases of waves affected the acceleration circumstances of leading edge.The wave on suction side could change the"spike"close to the leading edge,the action mechanism for waves changing transition position was related to the characteristics of the airfoil itself;when waves occurred before the location of transition,the variation of"spike"could change the location of transition.

关 键 词：压气机 波纹度 平面叶栅试验 气动性能 前缘转捩 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]