Study on influence of blade trailing edge structure on performance of axial flow fans

doi:10.3785/j.issn.1006-754X.2026.05.193

Chinese Journal of Engineering Design

2026, Vol. 33

Issue (2): 223-233 DOI: 10.3785/j.issn.1006-754X.2026.05.193

Optimization Design

Study on influence of blade trailing edge structure on performance of axial flow fans

Lang ZHANG(

),Kejun LI(

),Minya DENG,Bo WANG,Xinghua LI

School of Mechanical and Intelligent Manufacturing, Central South University of Forestry & Technology, Changsha 410004, China

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Abstract

To address the casting process problem caused by the convergence of the inscribed circle radius of the axial flow fan blade trailing edge contour to zero, the existing blade trailing edge thickening structure is researched, and a new type of blade trailing edge rounding structure is proposed. Through establishing a numerical simulation model of the axial flow fan, the air flow rate, total pressure, impeller power, total pressure efficiency and noise of the fans with different trailing edge structures were analyzed by the computational fluid dynamics method. The results showed that the maximum air flow rate of the fans with different trailing edge structures gradually decreased with the increase of trailing edge thickness. For every 0.5 mm increase in trailing edge thickness, the maximum air flow rate of the fans with thickening structure and rounding structure was reduced by 0.72% and 0.68%, respectively. Under the designed air flow rate, for every 0.5 mm increase in trailing edge thickness, the impeller power of the fans with thickening structure and rounding structure was reduced by 1.92% and 1.87%, the total pressure was decreased by 3.04% and 2.84%, and the total pressure efficiency was reduced by 0.47% and 0.62%. When the thickness l of the thickening structure was 2.5 mm, the noise near the impeller was the minimum, reaching 105.41 dB, which was 0.79 dB lower than that at l=0 mm. When the fillet diameter D of the rounding structure was 3.0 mm, the noise near the impeller was the minimum, reaching 104.91 dB, which was 1.29 dB lower than that at D=0 mm. By quantifying the impact of trailing edge thickness variations on the performance of axial flow fans, the casting process problem of the blade is solved, which provides a reference for the structural design of the blade trailing edge and the optimization of its aerodynamic performance.

Key words： axial flow fan blade trailing edge structure air flow rate total pressure total pressure efficiency impeller power acoustic performance

Received: 13 July 2025 Published: 28 April 2026

CLC:

TH 432.1

Corresponding Authors: Kejun LI E-mail: zl15770551720@163.com;likejuncsu@126.com

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Cite this article:

Lang ZHANG,Kejun LI,Minya DENG,Bo WANG,Xinghua LI. Study on influence of blade trailing edge structure on performance of axial flow fans. Chinese Journal of Engineering Design, 2026, 33(2): 223-233.

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https://www.zjujournals.com/gcsjxb/10.3785/j.issn.1006-754X.2026.05.193 OR https://www.zjujournals.com/gcsjxb/Y2026/V33/I2/223

叶片尾缘结构对轴流风机性能的影响研究

针对轴流风机叶片尾缘轮廓线内切圆半径收敛至零所引起的铸造工艺问题，对现有叶片尾缘加厚结构进行了研究，并提出了一种新型的叶片尾缘倒圆结构。通过建立轴流风机的数值仿真模型，使用计算流体力学方法对采用不同叶片尾缘结构时风机的风量、全压、叶轮功率、全压效率和噪声进行了仿真分析。结果表明：采用不同叶片尾缘结构时风机的最大风量均随尾缘厚度的增大而逐渐减小；尾缘厚度每增大0.5 mm，采用加厚结构和倒圆结构时风机的最大风量分别约降低0.72%和0.68%；在设计风量下，尾缘厚度每增大0.5 mm，采用加厚结构和倒圆结构时风机的叶轮功率分别约降低1.92%和1.87%，全压分别约降低3.04%和2.84%，全压效率分别约降低0.47%和0.62%。当加厚结构的厚度l=2.5 mm时，靠近叶轮处的噪声最小，为105.41 dB，较l=0 mm时减小了0.79 dB；当倒圆结构的圆角直径D=3.0 mm时，靠近叶轮处的噪声最小，为104.91 dB，较D=0 mm时减小了1.29 dB。通过量化尾缘厚度变化对轴流风机性能的影响，解决了叶片的铸造工艺问题，为叶片尾缘的结构设计及气动性能优化提供了参考。

关键词： 轴流风机, 叶片尾缘结构, 风量, 全压, 全压效率, 叶轮功率, 声学性能

Fig.1 Blade structure of axial flow fan

Fig.2 Physical model of axial flow fan

Fig.3 Mesh model of axial flow fan

Fig.4 Mesh independence validation result

Table 1 Main parameters of axial flow fan

Fig.5 Aerodynamic performance of axial flow fan

Fig.6 Diagram of blade trailing edge structure

Fig.7 Effect of trailing edge thickening structure on aerodynamic performance of axial flow fan

Fig.8 Total pressure distribution cloud maps at 50% blade height under different thicknesses l

Fig.9 Static pressure pulsation curves at blade tip under different thicknesses l

Fig.10 Noise spectrum diagrams at blade tip under different thicknesses l

Fig.11 Effect of trailing edge rounding structure on aerodynamic performance of axial flow fan

Fig.12 Axial velocity distribution cloud maps at 50% blade height under different fillet diameters D

Fig.13 Static pressure pulsation curves at blade tip under different fillet diameters D

Fig.14 Noise spectrum diagrams at blade tip under different fillet diameters D

Fig.15 Comparison of maximum air flow rate of axial flow fan

Fig.16 Comparison of impeller torque of axial flow fan (q=11.5 m³/s)

Table 2 Comparison of impeller power of axial flow fan (q=11.5 m³/s)

Fig.17 Comparison of total pressure of axial flow fan (q=11.5 m³/s)

Fig.18 Comparison of vorticity distribution in impeller area of axial flow fan (q=11.5 m³/s)

Fig.19 Comparison of total pressure efficiency of axial flow fan (q=11.5 m³/s)

Fig.20 Comparison of static pressure pulsation curves at blade tip with trailing edge thickness of 1.5 mm (q=11.5 m³/s)

Fig.21 Comparison of noise spectrum diagrams at blade tip with trailing edge thickness of 1.5 mm (q=11.5 m³/s)


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