尾迹扫掠下超高负荷低压涡轮叶片附面层特性  

Boundary layer behaviors on an ultra-high-lift low-pressure turbine profile under unsteady wakes

作　　者：李伟[1,2] 张波[1,2] 周敏[3] 卢新根[1] 朱俊强[1] 

机构地区：[1]中国科学院工程热物理研究所轻型动力重点实验室,北京100190 [2]中国科学院研究生院,北京100190 [3]北京航空工程技术研究中心,北京100076

出　　处：《航空动力学报》2012年第1期176-182,共7页Journal of Aerospace Power

基　　金：国际科技合作项目(2010DFB70620);国家自然科学基金(51176187)

摘　　要：利用表面热膜测量上游尾迹周期性扫掠下某超高负荷低压涡轮叶片吸力面附面层的非定常流动特性.通过热膜测得的准壁面剪切力及其统计参数云图分析了尾迹与附面层的相互作用对分离、转捩及再附过程的影响.实验结果表明:对于低雷诺数Re超高负荷产生较大分离泡的情形,尾迹扫掠对涡轮叶片附面层的发展具有显著影响,能够有效地抑制附面层的流动分离.An experimental investigation on unsteady boundary layer behaviors of the suction surface of an ultra-high-lift low pressure turbine profile under periodically unsteady wakes was conducted with the help of surface-mounted hot film, and the influence of the wake-boundary layer interaction on the boundary layer separation, transition and reattach- ment was analyzed in detail with space-time（S-T） diagrams of quasi-wall shear stress and statistical parameters. The experimental results show that the wake has a significant influ- ence on the boundary layer of turbine profile and the separation has been remarkably sup- pressed despite the larger separation bubble on the suction surface of ultra-high-lift profile at low Reynolds number.

关 键 词：尾迹扫掠 超高负荷 低压涡轮 转捩 表面热膜 

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]