Effect of blade sweep on inlet flow in axial compressor cascades

• Published in: Chinese journal of aeronautics 2015-02, Vol.28 (1), p.103-111
• Main Authors: Chang, Hao, Zhu, Fang, Jin, Donghai, Gui, Xingmin
• Format: Article
• Language: English
• Subjects: Axial compressors; Blades; Cascade; Cascades; Circumferences; Circumferentially averaged; Compressors; Computational fluid dynamics; Inlet flow; Mathematical analysis; Mathematical models; Radial transfer; Sweep; 入口流量; 叶栅; 叶片; 平均流场; 数值模拟; 计算流体动力学; 轴流压缩机; 进口
• ISSN: 1000-9361
• DOI: 10.1016/j.cja.2014.12.023

This paper presents comparative numerical studies to investigate the effects of blade sweep on inlet flow in axial compressor cascades. A series of swept and straight cascades was modeled in order to obtain a general understanding of the inlet flow field that is induced by sweep.A computational fluid dynamics（CFD） package was used to simulate the cascades and obtain the required three-dimensional（3D） flow parameters. A circumferentially averaged method was introduced which provided the circumferential fluctuation（CF） terms in the momentum equation.A program for data reduction was conducted to obtain a circumferentially averaged flow field.The influences of the inlet flow fields of the cascades were studied and spanwise distributions of each term in the momentum equation were analyzed. The results indicate that blade sweep does affect inlet radial equilibrium. The characteristic of radial fluid transfer is changed and thus influencing the axial velocity distributions. The inlet flow field varies mainly due to the combined effect of the radial pressure gradient and the CF component. The axial velocity varies consistently with the incidence variation induced by the sweep, as observed in the previous literature. In addition, factors that might influence the radial equilibrium such as blade camber angles, solidity and the effect of the distance from the leading edge are also taken into consideration and comparatively analyzed.