摘要
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.
基金
the Institutional support(RVO 61388998)
the Technology Agency of the Czech Republic(Grant TA02020057)
support from the Center of Advanced Aerospace Technology(CZ.02.1.01/0.0/0.0/16019/0000826)
Centre for Advanced Applied Science(CZ.02.1.01/0.0/0.0/1619/0000778)。
作者简介
Corresponding author:LOUDA Petr,E-mail:petr.louda@fs.cvut.cz。
