叶尖小翼对高亚声速扩压叶栅气动特性影响的数值研究  

Numerical simulation of blade tip winglet on the aerodynamic performance of high subsonic compressor cascade

作　　者：吴宛洋 钟兢军[1] 韩少冰[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《大连海事大学学报》2017年第2期97-102,共6页Journal of Dalian Maritime University

基　　金：国家自然科学基金重点项目(51436002);国家自然科学基金青年科学基金项目(51406021);中央高校基本科研业务费专项资金资助项目(3132014319;3132016334);辽宁省高等学校创新团队支持计划资助项目(LT2015004)

摘　　要：压气机正逐渐向着高负荷、高稳定性的方向发展.为有效控制该趋势下间隙区域内的流动损失加剧现象,可在高亚声速的扩压叶栅中加装叶尖小翼.本文对原型叶片及不同宽度的压力面与吸力面叶尖小翼叶片进行数值研究.结果表明:高亚声速下不同安装方案下的叶尖小翼均可以改善压气机的气动特性,削弱泄漏涡的强度,其中,压力面小翼对于流场的改善效果更为明显,与原型相比,PW2.0的总压损失系数降低了4.47%.The compressor is developing towards high load and high stability,so in order to reduce the loss of the clearance area under this trend,the winglet could be used in the high subsonic cascade. Numerical simulation was carried out to investigate the effect of different shapes of tip winglets. Results show that an improved aerodynamic performance and a weakened tip leakage is achieved by using different winglets. The improvement effect of the pressure side winglet is more obvious,and the total pressure loss coefficient of PW2. 0 is reduced by 4. 47% compared with the prototype.

关 键 词：高亚声速 扩压叶栅 叶尖小翼 数值模拟 

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]