• 论文 •

### S弯进气道出口旋流对轴流压气机性能的影响

1. 空军工程大学 航空工程学院, 西安 710038
• 收稿日期:2020-05-15 发布日期:2021-08-06
• 通讯作者: 程邦勤 E-mail:1695438620@qq.com

### Effects of swirl at outlet of S-shaped inlet on axial flow compressor performance

WANG Jiale, CHENG Bangqin, FEI Xiaowen, YU Yang, FENG Luning

1. Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China
• Received:2020-05-15 Published:2021-08-06

Abstract: In order to estimate the effects of swirl at outlet of S-shaped inlet on the performance of axial flow compressor, a swirl distortion network was optimized and designed to simulate the swirl flow field. The aerodynamic response of the single-stage axial flow compressor under the effect of the swirl at the outlet of the S-shaped inlet was investigated by numerical simulation. The characteristic map and flow field distributions of the compressor under the condition of uniform intake and swirling intake were obtained. The results show that the overall swirl angle error of the optimized swirl distortion network is reduced. The swirl flow at the outlet of S-shaped inlet has little influence on the pressurization ability, but it will lead to the decrease of compressor efficiency and decrease of stability. At the corrected speed of 100% and 80%, the maximum reduction of pressure ratio is 0.12% and 0.28% respectively, and the maximum reduction of efficiency near the peak efficiency point is 3.2% and 14.4% respectively. The reverse swirl zone in the swirl at the outlet of the S-shaped inlet increases the inlet attack angle of the rotor blade, resulting in the separation of airflow at the suction side and the blockage of the blade passage, which eventually leads to the instability of the compressor.