The Numerical Investigation of Asymmetric Boundary Layer Suction in High-load Compressor Cascades

被引：0

作者：

Lu, Hua-Wei ^{[1
]}

Wang, Xu ^{[1
]}

Guo, Shuang ^{[2
]}

Huang, Yu-Xuan ^{[1
]}

Zheng, Yu-Chen ^{[1
]}

Zhang, Hai-Xin ^{[1
]}

Zhong, Jing-Jun ^{[1
]}

机构：

[1] School of Naval Architecture and Ocean Engineering, Dalian Maritime University, Dalian,116026, China

[2] School of Aeronautics and Astronautics, Dalian University of Technology, Dalian,116024, China

来源：

Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics | 2018年 / 39卷 / 05期

关键词：

Boundary layers - Numerical methods - Compressors;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

This paper investigates the influence of asymmetric boundary layer suction through endwall holes on aerodynamic performance in large turning angle compressor cascades. Numerical methods verified by experiment, the suction position located at endwall near suction surface, four suction schemes are divided along the chord length of the cascades, the calculating domain includes cavity. Results show the boundary layer suction on endwall that cover separation point could improve the corner flow condition of the suction side, delay flow separation and reduce losses. But adverse effects arise on corner of the other side without suction, such as earlier flow separation and larger range of corner separation. © 2018, Science Press. All right reserved.

引用

页码：977 / 984