ABSTRACT The splitter blades are widely used in axial compressors and play an active role in the improvement of the overall performance of compressors. However, little research on the application of splitter blades to small axial flow fans is conducted. This paper designs a splitter blade small axial flow fan (model B) with a small axial flow fan as the prototype fan (model A) by adding short blades at the second half part of the passageway among long blades of model A. The steady simulation for the two models was conducted with the help of RNG k-ε turbulence model provided by software Fluent, and static characteristics and internal flow characteristics of the two models were compared and analyzed. Results show that splitter blades can improve the unsteady flow in the small flow rate region and also have a positive role to increase static pressure rise and efficiency in the higher flow rate region. The variation of static pressure gradient on the meridian plane in model B is well-distributed. The static pressure on the blade surface of model B distributes more uniformly. Splitter blades can suppress the secondary flow from pressure side to suction side in the leading edge because the pressure difference between suction side and pressure side in model B is generally lower than that of model A. And it also can restrain the vortex shedding and flow separation, and further it may be able to get the aerodynamic noise lower because static pressure gradient on the blade surface is well-distributed and the vortex shedding is not developed. Therefore, the performance of the fan with splitter blades is better than that of the prototype fan. The findings of this paper can be a basis for the design of high performance small axial flow fans.
Cite this paper
L. Zhu, Y. Jin, Y. Jin, Y. Wang and L. Zhang, "Numerical Study on Internal Flow of Small Axial Flow Fan with Splitter Blades," Open Journal of Fluid Dynamics, Vol. 3 No. 2, 2013, pp. 75-80. doi: 10.4236/ojfd.2013.32A012.
 J. F. Zhang, Y Yuan, L. T. Ye, et al., “Research State of The Centrifugal Machineries with Impeller Adding Splitter Blades,” Fluid Machinery, Vol. 39, No. 11, 2011, pp. 38-44.
 A. J. Wennerstrom and G. R. Frost, “Design of a Rotor Incorporating Splitter Vanes for a High Pressure Ratio Supersonic Axial Compressor Stage,” United States Air Force Systems Command, ARL-TR-74-0110, 1974.
 A. J. Wennerstrom, “Test of a Supersonic Axial Compressor Stage Incorporating Splitter Vanes in The Rotor,” United States Air Force Systems Command, ARL-TR-75-0165, 1975.
 X. Qiu and T. Dang, “Three-Dimension Inverse Method for Turbomachine Blading with Splitter Blades,” ASME Paper, 2000-GT-0526, 2000.
 H. P. Li and H. X. Liu, “Numerical Simulation Analysis of Leakage Flow in Compressor Cascade with Splitter,” Journal of Beijing University of Aeronautics and Astro nautics, Vol. 33, No. 1, 2007, pp. 31-34.
 H. P. Li and H. X. Liu, “Analysis of Flow Mechanism in 2-D Compressor Cascade with Splitter,” ASME Paper, GT-2005-68207, 2005.
 K. L. Tzuoo, S. S. Hingorani and A. K. Sehra, “Optimization of a Highly-Loaded Axial Splittered Rotor Design,” Revue Francaise de Mecanique, Vol. 1, No. 3, 1992, pp. 235-246.
 Y. X. Zhang, Z. P. Zou, M. Yan and M. Z. Chen, “Flow Analysis of a Single-Stage Axial Flow Compressor with Splitter Rotor,” Journal of Aerospace Power, Vol. 19, No. 1, 2004, pp. 89-93.
 M. Yan and M. Z. Chen, “Flow Performance Analysis in an Axial Compressor Rotor with Splitter,” Journal of Propulsion Technology, Vol. 24, No. 4, 2002, pp. 280-282.
 X. M. Sun, P. G. Yan, S. T. Wang and Q. Zhong, “Investigation of the Influence of Splitter Chord Length on the Transonic Axial Fan Rotor,” Journal of Aerospace Power, Vol. 22, No. 12, 2007, pp. 2050-2054.
 L. Xue and W. J. Han, “Effects of Circumferential Configuration Concerning Splitter Blade on the Aerodynamic Performance in a Transonic Axial Fan,” Journal of Harbin Institute of Technology, Vol. 17, No. 1, 2010, pp. 75-81.