基于任意多项式中弧线的单级高效率风扇设计
Design of single stage high efficiency fan based on arbitrary polynomial camber line airfoils
Received date: 2016-08-01
Revised date: 2016-09-26
Online published: 2016-10-14
为了在压气机通流设计阶段考虑叶片弯掠效应，开发了基于流线曲率法的通流设计程序，提出一种基于四次多项式的任意中弧线叶片造型方法，并推导了任意回转面上的中弧线表达式。以此方法为基础，采用通流设计与叶片造型相互迭代的方式开展大流量跨声速风扇设计研究。此风扇级的设计点为巡航状态，设计流量为155 kg/s、压比为1.54。研究结果表明：在设计状态，此风扇级的总压比为1.545，转子和级效率分别为0.939、0.916；在设计转速下，失速裕度为17%，转子和级最高效率分别为0.945、0.923；在起飞状态，流量接近440 kg/s，效率与巡航状态相当，压比高于巡航状态。
邱名 , 郝颜 , 范召林 , 江雄 , 陈逖 . 基于任意多项式中弧线的单级高效率风扇设计[J]. 航空学报, 2017 , 38(5) : 120657 -120657 . DOI: 10.7527/S1000-6893.2016.0262
To adequately consider the blade lean and sweep influence on compressor performance in the stage of through-flow design, a through-flow design program is developed basing on streamline curvature approach, and a blade airfoils generating method is introduced basing on arbitrary camber lines. The camber lines is expressed on arbitrary rotary surface in the investigation. Basing on these methods, a single stage transonic fan is designed. The designing is done through the iteration between through-flow designing with blade geometry generating. The cruise state, in which the mass flow is 155 kg/s and pressure-ratio is 1.54, is treated as design state in the investigation. The results show that the pressure-ratio is 1.545, and rotor efficiency of 0.939, stage efficiency of 0.916 at design state. At the design speed, the stall margin is 17%, and the highest rotor (stage) efficiency is 0.945 (0.923). The mass flow is close to 400 kg/s, and efficiency increases a litter, pressure-ratio obviously rises at off state.
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