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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
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.
QIU Ming, HAO Yan, FAN Zhaolin, JIANG Xiong, CHEN Ti. Design of single stage high efficiency fan based on arbitrary polynomial camber line airfoils[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(5): 120657-120657. DOI: 10.7527/S1000-6893.2016.0262
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