跨音压气机基于前掠和小翼联合扩稳方法研究  

Study on the Stability Enhancement of Transonic Compressor Combined With Forward Sweep and Winglet

作　　者：崔伟伟 李超 刘付松 王兴鲁 姚飞 王翠苹 刘玉峰 CUI Wei-Wei;LI Chao;LIU Fu-Song;WANG Xing-Lu;YAO Fei;WANG Cui-Ping;LIU Yu-Feng(College of Civil Engineering and Architecture,Shandong University of Science and Technology,Qingdao 266590,China;Key Laboratory of Civil Engineering Disaster Prevention and Mitigation of Shandong Province,Qingdao 266590,China;Qingdao Hisense Hitachi Air-Conditioning Systems Co.Ltd,Qingdao 266071,China)

机构地区：[1]山东科技大学土木工程与建筑学院,青岛266590 [2]山东省土木工程防灾减灾重点实验室,青岛266590 [3]青岛海信日立空调系统有限公司,青岛266071

出　　处：《工程热物理学报》2021年第6期1423-1430,共8页Journal of Engineering Thermophysics

基　　金：国家自然科学基金面上项目(No.52076124);山东省自然科学基金面上项目(No.ZR2020ME173)。

摘　　要：针对NASA的Rotor37转子,采用数值方法详细研究了气动前掠和压力面叶尖小翼两种控制方法对其总体性能和叶尖流场结构的影响机制。数值结果表明,单独采用前掠和同时采用前掠和小翼联合作用分别使压气机稳定工作范围提升20.1%和27.7%,且对压气机的效率和增压比影响较小。气动前掠一定程度上抑制了间隙区泄漏流引发的气动损失及低速区范围,但是会导致尖区边界层分离及损失明显增加。相比之下,压力面叶尖小翼对由泄漏流诱发的低速区和吸力面边界层分离区均有较好的抑制效果,从而实现压气机稳定工作范围的明显提升。此外,气动前掠和叶尖小翼的作用效果也表明,转子叶顶的静压差虽然是间隙泄漏流的直接驱动力,但不是影响泄漏流强度和作用范围的唯一因素。The effects of forward sweep and pressure-surface tip winglet on the performance and tip flow structure of NASA’s Rotor 37 were investigated numerically.The results show the stable operating range of rotor has increased by 20.1%and 35.4%when the single forward sweep and combined method with forward sweep and pressure-surface tip winglet are utilized respectively,with a few negative effects on the efficiency and pressure ratio.The forward sweep reduces the loss and low-velocity region in some extent,but it increases the boundary layer separation and additional loss in tip region.By contrast,the pressure-side tip winglet has a better suppression effect on the low-velocity region induced by leakage flow and the boundary layer separation near suction surface,and produces an obvious increase of stable operating range of rotor.Moreover,although the static pressure difference near blade tip is the direct driving force of leakage flow,it is not the only factor affecting the strength and affected range of leakage flow.

关 键 词：气动前掠 叶尖小翼 通道激波 泄漏流 流动扩稳 

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]