A novel approach for the design of axial flow fan by increasing by-pass ratio in a constantdiameter turbofan
作者机构：Department of Mechanical Engineering.Isfahan University of TechnologyIsfahan***Iran
出 版 物：《Propulsion and Power Research》 (推进与动力（英文）)
年 卷 期：2020年第9卷第2期
页 面：142-158页
核心收录：
学科分类：07[理学] 0701[理学-数学] 070101[理学-基础数学]
主 题：Axial flow fan Bypass ratio Computer simulation Design methodology Thermodynamic turbofan cycle analysis
摘 要：The present study introduces an innovative aerodynamic redesign of an axial flow fan based on constant diffusion factor and radial *** 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 *** new designed fan flow field is investigated in detail by CFD tool at both design and off design ***,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 *** 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 ***,efficiency reduction in fan over speed is the main disadvantage.
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