A THREE-DIMENSIONAL NUMERICAL ANALYSIS OF THE FLOW FIELD FOR FAN/COMPRESSOR WITH STEADY-STATE INLET DISTORTION

摘要：

A Model used to calculate the performance of axial flow fan/compressor with/without distorted inlet flow was presented in this paper. The modified compressible, time-dependent, 3D Euler equations including the turbomachinery source terms which represent the effect of the blades were solved to simulate the 3D flow filed of fan/compressor. The source terms were calculated for each blade row by the use of a streamline curvature code. Details of the overall approach were presented and verified with NASA Rotor-67 fan for the clean/distorted inlet flow. The predicted results agree well with the available experimental data.

作者: Xu Kaifu Qiao Weiyang Wang Limin

作者单位: School of Engine and Energy, Northwestern Polytechnical University Xian, 710072 P.R.China

会议类型: 国际会议

会议名称: 第一届喷气推进与动力工程国际会议(Proceedings of the 1st International Symposium on Jet Propulsion and Power Engineering)

会议地点: 昆明

会议语种:英文

页码: 386-390

在线出版日期: 2006-09-18（万方平台首次上网日期，不代表论文的发表时间）