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A study of 3D aerodynamic design for a transonic compressor blading optimized by the locations of aerofoil maximum thickness and maximum camber

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Abstract

A design procedure for improving the efficiency of a transonic compressor blading was proposed based on a rapid generation method for three-dimensional blade configuration and computational meshes, a three-dimensional Navier-Stokes solver and an optimization approach. The objective of the present paper is to design a transonic compressor blading optimized only by selection of the locations of maximum camber and maximum thickness for the airfoils at different span heights and to study how do these two design parameters affect the blade performance. The blading configuration and the computational meshes can be obtained very rapidly for any given combination of maximum camber and maximum thickness. The computational grid system generated is used for the Navier-Stokes solution to predict adiabatic efficiency, total pressure ratio and flow rate. As a main result of the optimization, adiabatic efficiency was successfully improved.

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Authors and Affiliations

  1. Institute of Engineering Thermophysics, Chinese Academy of Sciences, P.O. Box 2706, 100080, Beijing, China

    Naixing Chen, Hongwu Zhang, Yanji Xu & Weiguang Huang

Authors
  1. Naixing Chen
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  2. Hongwu Zhang
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  3. Yanji Xu
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  4. Weiguang Huang
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Chen, N., Zhang, H., Xu, Y. et al. A study of 3D aerodynamic design for a transonic compressor blading optimized by the locations of aerofoil maximum thickness and maximum camber. J. of Therm. Sci. 12, 198–203 (2003). https://doi.org/10.1007/s11630-003-0067-z

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  • DOI: https://doi.org/10.1007/s11630-003-0067-z

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