The present study introduces an innovative aerodynamic redesign of an axial flow fan based on constant diffusion factor and radial equilibrium. All input design parameters such as mass flow rate, hub to tip ratio, aspect ratio, tip diameter and angular velocity are taken from NASA Rotor 67 as a conventional axial flow fan. A computer program is developed to extract the three-dimensional geometry of a fan and to estimate the span-wise distribution of parameters. The new designed fan flow field is investigated in detail by CFD tool at both design and off design conditions. Finally, a turbofan cycle analysis is conducted based on thermodynamic and gas dynamic principles to evaluate the fan performance in a turbofan engine in comparison to NASA Rotor 67. Achieving a higher total pressure ratio, meeting the target pressure ratio in lower rotational speed with higher efficiency, delivering more bypass air in a constant diameter and less fuel consumption for the same specific thrust force are the main advantages for the new design strategy in comparison to the conventional designed fans such as Rotor 67. However, efficiency reduction in fan over speed is the main disadvantage.

本研究介绍了基于恒定扩散因子和径向平衡的轴流风扇的创新空气动力学设计。所有输入设计参数（例如质量流率，轮毂与叶尖之比，纵横比，叶尖直径和角速度）均从NASA转子67作为常规轴流风扇获得。开发了计算机程序以提取风扇的三维几何形状并估计参数的跨度分布。在设计和非设计条件下，CFD工具都会对新设计的风扇流场进行详细研究。最后，根据热力学和气体动力学原理进行涡轮风扇循环分析，以评估涡轮风扇发动机与NASA转子67相比的风扇性能。实现更高的总压力比，