基于油流图谱的高负荷压气机叶栅叶顶涡系研究  

Research on vortex structure near tip clearance in a highly loaded compressor cascade based on oil flow pattern

作　　者：高丽敏[1] 蔺世彦 李瑞宇 赵磊[1] GAO Limin;LIN Shiyan;LI Ruiyu;ZHAO Lei(National Key Laboratory of Aerodynamic Design and Research,School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;School of Aerospace Engineering,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]西北工业大学动力与能源学院翼型、叶栅空气动力学国家级重点实验室,西安710129 [2]西安交通大学航空航天学院,西安710049

出　　处：《航空动力学报》2023年第10期2473-2482,共10页Journal of Aerospace Power

基　　金：国家自然科学基金重点项目(51790512)。

摘　　要：对某高负荷扩压叶栅的叶顶间隙流动进行不同来流攻角和马赫数下的油流实验以及数值模拟,通过对油流图谱进行拓扑分析,同时辅以数值模拟结果,从近壁面和流场空间共同对叶顶区域的涡系结构及其随负荷变化的规律进行了研究。结果显示,高负荷压气机扩压叶栅叶顶区域存在6个关键的涡结构:叶尖泄漏涡、叶顶分离涡、叶尖二次涡、马蹄涡、通道涡和诱导涡;来流攻角的增加会导致叶片负荷增大以及负荷分布变化,引起最大压差位置提前,导致泄漏提前发生,对流场涡系结构影响较为明显;而来流马赫数的变化对涡系结构的影响较小。Through the oil flow experiments on the tip clearance flow of a highly loaded compressor cascade under different attack angles and Mach numbers,the oil flow patterns on the tip wall and suction surface of the blade were clearly captured,and the vortex structure of the blade tip was studied by topological analysis.The results showed that there existed six key vortices in the tip region of the compressor blade:tip leakage vortex,tip separation vortex,tip secondary vortex,horseshoe vortex and induced vortex;the increase of the attack angle of the incoming flow led to the increase of the blade load and the change of load distribution,the position of the maximum pressure difference was advanced,leading to the leakage in advance,yielding an obvious influence on the vortex structure of the flow field.On the contrary,the change of Mach number had little effect on the vortex structure.

关 键 词：高负荷压气机 叶顶间隙 油流图谱 叶尖泄漏涡 涡系干涉 

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]