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Study on the Numerical Model of Transonic Wind Tunnel Test Section

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Abstract

The authors consider numerical simulations of transonic flows through various turbine cascades in a confined channel which approximates boundaries of real wind tunnel. The boundaries of the wind tunnel are impermeable or there can be permeable tailboards to diminish shock wave reflections. The mathematical model is based on Favre-averaged Navier-Stokes equations closed by a turbulence model and model of transition to turbulence. The mathematical model is solved by an implicit finite volume method with multi-block grids. Several types of turbine blade cascades with subsonic or supersonic inlet are presented. The results are compared with optical measurements and simulations of periodic cascades. The validity of experimental reference flow parameters in relation to computed flow patterns is discussed.

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Acknowledgments

The work was supported by the Institutional support (RVO 61388998) and by the Technology Agency of the Czech Republic (Grant TA02020057). Authors also acknowledge support from the Center of Advanced Aerospace Technology (CZ.02.1.01/0.0/0.0/16019/0000826) and Centre for Advanced Applied Science (CZ.02.1.01/0.0/0.0/16 19/0000778).

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Authors and Affiliations

  1. Institute of Thermomechanics of the Czech Academy of Sciences, Prague 8, 18200, Czech Republic

    Petr Louda & Jaromír Příhoda

  2. Faculty of Mechanical Engineering, Czech Technical University, Prague 2, 12135, Czech Republic

    Petr Louda

Authors
  1. Petr Louda
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  2. Jaromír Příhoda
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Correspondence to Petr Louda.

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Louda, P., Příhoda, J. Study on the Numerical Model of Transonic Wind Tunnel Test Section. J. Therm. Sci. 30, 231–241 (2021). https://doi.org/10.1007/s11630-020-1277-3

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  • DOI: https://doi.org/10.1007/s11630-020-1277-3

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