不同间隙下叶尖小翼对高亚声速扩压叶栅气动特性的影响研究  

Effect of Blade Tip Winglet on Aerodynamic Performance of High Subsonic Compressor Cascade at Different Tip Clearances

作　　者：钟兢军[1] 吴宛洋 王会社[2] ZHONG Jing-Jun1, WU Wan-Yang1, WANG Hui-She2(1. Marine Engineering College, Dalian Maritime University, Dalian 116026, China 2. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, Chin)

机构地区：[1]大连海事大学轮机工程学院,大连116026 [2]中国科学院工程热物理研究所,北京100190

出　　处：《工程热物理学报》2018年第4期757-766,共10页Journal of Engineering Thermophysics

基　　金：国家自然科学基金项目(No.51436002;No.51406021);中央高校基本科研业务费专项资金资助(No.3132016014;No.3132017001);辽宁省高等学校创新团队支持计划资助项目(No.LT2015004);辽宁省博士科研启动基金资助项目(No.201601078)

摘　　要：为了全面探究压力面小翼对于叶顶间隙流动的影响机理,通过数值模拟软件ANSYS CFX对高亚声速不同间隙下的常规叶栅和压力面侧具有不同叶尖小翼的扩压叶栅进行了数值计算.结果表明:在进口气流速度Ma=0.7时,与常规叶栅相比,T=1%h、τ=2%h及τ=3%h三种间隙高度下的不同宽度压力面小翼都可以削弱泄漏涡的强度,控制间隙流动,降低扩压叶栅的流动损失,最佳小翼方案随着间隙变化有所不同,当τ=3%h,压力面小翼展现了最明显的改善效果,在压力面小翼的宽度为常规叶栅叶顶宽度的1.5倍时,与同间隙下的常规叶栅相比,总压损失系数降低了9.2%.In order to completely investigate the effect mechanism of the pressure side winglet on tip clearance flow, the numerical simulation has been carried out to explore the original cascade and cascades with different pressure side winglets at different tip clearances by using the ANSYS CFX software. The results show that when incoming flow Mach number is 0.7, the pressure side winglet can reduce the intensity of tip leakage vortex and control the tip clearance flow at three tip clearances of τ=1%h, τ=2%h and τ=3%h, thus the total pressure loss of the cascade is decreased. Different tip clearances gain various best winglet schemes. When the tip clearance is 3%h,the pressure side winglet shows the most obvious improvement, and the most effective pressure side winglet is PW1.5, which provides the aerodynamic loss reduction by 9.2 percent compared to original cascade at the same tip clearance.

关 键 词：叶顶间隙 扩压叶栅 叶尖小翼 高亚声速 叶顶泄漏 

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]