Blade shape optimization for transonic axial flow fan

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• 作者：Peng Song (1) (2)
  Jinju Sun (1) (2)
  
  1. School of Energy and Power Engineering ; Xi鈥檃n Jiaotong Univ. ; 28 West Xianning Road ; Xi鈥檃n ; 710049 ; China
  2. Collaborative Innovation Center for Advance Aero-Engine (CICAAE) ; 37 Xueyuan Road ; Beijing ; 100191 ; China
  
• 关键词：Transonic axial flow fan ; CFD ; Geometry parameterization ; Global optimization ; Stacking line
• 刊名：Journal of Mechanical Science and Technology
• 出版年：2015
• 出版时间：March 2015
• 年：2015
• 卷：29
• 期：3
• 页码：931-938
• 全文大小：1,159 KB
• 参考文献：1. Pierret, S., Braembussche, R. V. (1999) Turbomachinery blade design using a Navier-Stokes solver and artificial neural network. Journal of Turbomachinery 121: pp. 326-332 CrossRef
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  3. Lian, Y., Liou, M.-S. (2005) Multi-objective optimization of transonic compressor blade using evolutionary algorithm. Journal of Propulsion and Power 21: pp. 979-87 CrossRef
  4. Samad, A., Kim, K. (2008) Multi-objective optimization of an axial compressor blade. Journal of Mechanical Science and Technology 22: pp. 999-1007 CrossRef
  5. Pierret, S., Coelho, R. F., Kato, H. (2007) Multidisciplinary and multiple operating points shape optimization of three-dimensional compressor blades. Structural and multidisciplinary optimization 33: pp. 61-70 CrossRef
  6. Lotfi, O., Teixeira, J., Ivey, P., Kinghorn, I., Sheard, A. (2006) Shape optimisation of axial fan blades using genetic algorithms and a 3D Navier-Stokes solver. American Society of Mechanical Engineers, Barcelona, Spain.
  7. Samad, A., Kim, K. (2008) Shape optimization of an axial compressor blade by multi-objective genetic algorithm. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 222: pp. 599-611
  8. Okui, H., Verstraete, T., Braembussche, R. V., Alsalihi, Z. (2011) Three dimensional design and optimization of a transonic rotor in axial flow compressors.
  9. Benini, E., Biollo, R. (2007) Aerodynamics of swept and leaned transonic compressor-rotors. Applied energy 84: pp. 1012-1027 CrossRef
  10. Passrucker, H., Engber, M., Kablitz, S., Hennecke, D. (2003) Effect of forward sweep in a transonic compressor rotor. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 217: pp. 357-365
  11. Song, P., Sun, J., Wang, K., He, Z. (2011) Development of an optimization design method for turbomachinery by incorporating the cooperative coevolution genetic algorithm and adaptive approximate model.
  12. Strazisar, A. J., Wood, J. R., Hathaway, M. D., Suder, K. L. (1989) Laser anemometer measurements in a transonic axial-flow fan rotor.
  13. ANSYS CFX HELP MANUAL.
  14. Miller, P. L. (2000) Blade geometry description using B-splines and general surfaces of revolution.
  
• 刊物类别：Engineering
• 刊物主题：Mechanical Engineering
  Structural Mechanics
  Control Engineering
  Industrial and Production Engineering
  
• 出版者：The Korean Society of Mechanical Engineers
• ISSN：1976-3824

文摘

Transonic axial flow fan has relatively high blade tip speed and produces higher pressure ratio than the subsonic. However, considerable losses are brought about by the shock waves close to blade tip and over part of span, leading to deteriorated overall efficiency and operating flow range. The present study is to mitigate shock wave and reduce losses through simultaneous variation of blade sectional profiles and their stacking line in blade design. Both sectional profiles and stacking line are varied simultaneously to provide more flexible blade shape tuning. To achieve a best blade shape and produce maximum performance gains, a global optimization method is incorporated in the blade shape design. It includes an improved CCEA (cooperative co-evolution algorithm) optimizer and one-stage Expected Improvement (EI) based adaptively updated Kriging surrogate model. The former has divided the high-dimension optimization problems into readily solved low-dimension ones, while the later has enabled the optimizer to jump out of from the local optima and search the solution towards the global optima. The optimization is conducted for Rotor67 at design condition with a single workstation, and considerable overall efficiency and pressure ratio gains are simultaneously obtained, while the flow range is also extended. This is supported by the significantly improved flow behavior in the optimized blade passages, where the chordwise shock wave is mitigated, leading to an increase in overall efficiency; the spanwise static pressure distribution is improved evidently and this improves the overall pressure ratio.