International Journal of Fluid Machinery and Systems

Korean Society for Fluid machinery (한국유체기계학회)
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A Design Method for Cascades Consisting of Circular Arc Blades with Constant Thickness

  • Bian, Tao (Institute for Interdisciplinary Research, Jianghan University) ;
  • Han, Qianpeng (School of Electromechanical and Architectural Engineering, Jianghan University) ;
  • Bohle, Martin (Institute of Fluid Mechanics and Fluid Machinery, Technical University Kaiserslautern)
  • Received : 2016.07.05
  • Accepted : 2017.01.12
  • Published : 2017.03.31
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Abstract

Many axial fans have circular arc blades with constant thickness. It is still a challenging task to calculate their performance, i.e. to predict how large their pressure rise and pressure losses are. For this task a need for cascade data exists. Therefore, the designer needs a method which works quickly for design purposes. In the present contribution a design method for such cascades consisting of circular arc blades with constant thickness is described. It is based on a singularity method which is combined with a CFD-data-based flow loss model. The flow loss model uses CFD-data to predict the total pressure losses. An interpolation method for the CFD-data are applied and described in detail. Data of measurements are used to validate the CFD-data and parameter variations are conducted. The parameter variations include the variation of the camber angle, pitch chord ratio and the Reynolds number. Additionally, flow patterns of two dimensional cascades consisting of circular arc blades with constant thickness are shown.

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References

  1. Cumpsty, N. A., 2004, Compressor Aerodynamics. Krieger Publishing Company, Malabar, Florida.
  2. Eck, B. 2003, Fans, Springer Verlag, Berlin.
  3. ANSYS 2014, Software Package (Version 14.0), Centerra Resource Park, 10 Cavendish Court, Lebanon, NH 03766.
  4. Katz, J., and Plotkin, A. 2010. Low Speed Aerodynamics, Cambridge University Press, NewYork, NY.
  5. Lakshminaryana, B. 1996, Fluid Dynamics and Heat Transfer of Turbomachinery, John Wiley & Sons, Inc.,New York.
  6. Lewis, R. I. 1996, Turbomachinery Performance Analysis, John Wiley, NewYork, NY.
  7. Li, W. 2011, "Head Curve of Noncavitating Inducers," ASME Journal of Fluid Engineering, Vol. 133 (p.101104).
  8. Lieblein, S. 1965, "Aerodynamical Design of Axial-Flow Compressors," NASA SP-36. USA.
  9. Lindemann, T. B., Friedrichs, J. and Stark, U., 2014, "Development of a New Design Method for High Efficient Swept Low Pressure Axial Fans with Small Hub/Tip Ratio," ASME Turbo Expo, Dusseldorf, Germany, GT2014- 25932.
  10. Menter, F. R. 1994, "Two Equation Eddy-Viscosity Turbulence Models for Engineering Applications," AIAA Journal, Vol. 32,pp. 1598-1605. https://doi.org/10.2514/3.12149
  11. Menter, F. R., Langtry, R. B., Likki, S. R., Suzen, Y. B. and Huang, P. G., 2004, "A CorrelationBased Transition Model Using Local Variables, Part I - Model Formulation," ASME Turbo Expo, Vienna, Austria, GT2004-53452
  12. Roberts, W. B., 1973, "The Effect of Reynolds Number and Laminar Separation on Axial Cascade Performance," Journal of Engineering for Power, No. 74-GT-68.
  13. Schrapp, H., Stark, U., and Kosyna, G., 2006, "Cascade Investigations for Circular Arc Blades with Constant Thickness at Low Reynold Numbers," VDMA-Report No. L208, Frankfurt am Main, Germany.
  14. Stanitz, J. D., 1953, "Effect of Blade Thickness Taper and Axial Velocity Distribution at the Leading Edge of an Entrance Rotor Blade with Axial Inlet and the Influence of this Distribution on the Alignment of the Rotor Row for Zero Angle of Attack," NACA TN 2986. USA.
  15. Weinig, F. 1935, "The Flow Around Blades of Turbomachines," Verlag von Johann Ambrosius, Leipzig. Germany.