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Rapid meshing of turbomachinery rows using semi-unstructured multi-block conformal grids

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Abstract

A semi-unstructured grid generation method especially tailored for the meshing of turbomachinery blade passages and their associated cavities is presented. The method is based on a smart combination of quasi-3D methods, an ad hoc block decomposition of the domain and a grid-based solid-model-less reconstruction of the computational domain.

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Notes

  1. Parameter m′ is defined as follows:

    $$ m^{\prime}(x)=\int\nolimits_{x_{0}}^{x}{\frac{{\rm d}s}{r}}=\int\nolimits_ {x_{0}}^{x} {\frac{1}{r(x)}}\sqrt{1+\left(r^{\prime}(x)\right)^{2}}{\rm d}x $$

    where x is the axis of the engine. This parametrization is used in turbomachinery to deal with 2D CFD simulations on stream-surfaces since it preserves angles and is non-dimensional.

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Authors and Affiliations

  1. Universidad Politécnica de Cartagena, 30202, Cartagena, Spain

    Manuel A. Burgos

  2. Industria de TurboPropulsores, S.A., 28830, Madrid, Spain

    Juan M. Chia, Roque Corral & Carlos López

  3. Parque Empresarial San Fernando, ITP, Edificio J, 28830, San Fernando de Henares, Madrid, Spain

    Juan M. Chia, Roque Corral & Carlos López

Authors
  1. Manuel A. Burgos
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  2. Juan M. Chia
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  3. Roque Corral
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  4. Carlos López
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Correspondence to Manuel A. Burgos.

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Burgos, M.A., Chia, J.M., Corral, R. et al. Rapid meshing of turbomachinery rows using semi-unstructured multi-block conformal grids. Engineering with Computers 26, 351–362 (2010). https://doi.org/10.1007/s00366-009-0169-7

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  • DOI: https://doi.org/10.1007/s00366-009-0169-7

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