Volume 34 Issue 6
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Improved viscous inverse design method for three-dimensional turbomachinery blades[J]. Journal of Aerospace Power, 2019, 34(6): 1380-1388. doi: 10.13224/j.cnki.jasp.2019.06.021
Citation: Improved viscous inverse design method for three-dimensional turbomachinery blades[J]. Journal of Aerospace Power, 2019, 34(6): 1380-1388. doi: 10.13224/j.cnki.jasp.2019.06.021
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Improved viscous inverse design method for three-dimensional turbomachinery blades

doi: 10.13224/j.cnki.jasp.2019.06.021
  • Received Date: 2018-12-10
  • Publish Date: 2019-06-28
    Abstract
  • An improved inverse design method for three-dimensional turbomachinery blades in viscous flow field was proposed. It was assumed that the camber line had a virtual moving speed. The virtual movement was calculated by the difference between the target load and the actual load, and was reasonably limited by the thickness of viscous sublayer. The camber line was smoothed by cubic B-spline interpolation, and the new blade profile was obtained by updated camber line and the given blade thickness. Verification results show that the method can modify the blade profile according to the design intention. It has strong robustness, fast convergence speed, and high degree of freedom of the blade, independent of the specific grid and solver, and also it has certain generality.

     

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