Contribution to the numerical analysis of the internal cooling trailing edge geometry at stationary and rotating conditions

In this paper, a numerical aero-thermal validation has been carried out for two (02) 30:1 scaled models with ribbed internal surface representing a geometry of an original trailing edge (TE) composed of single row of seven enlarged pedestals in immobile and turning conditions for high Reynolds numbers. The commercial ANSYS-Fluent software is used to perform a CFD analysis modeling the isothermal air flow inside the stationary geometry by means of the k-ω SST turbulence model. PIV in addition to TLC experimental data were employed to verify the numerical model aero-thermally; qualitatively and quantitatively for different working conditions (Re = 10000-40000 and Ro = 0-0.23), respectively. Numerical results reveal, under rotating conditions, a disappearance of the observed horse-shoe structures of the stationary conditions inside the TE exit region, a decrease of the flow approaching angle and an acceleration of its velocity beside a surplus calculation of the turbulence Kinetic Energy (k). The obtained results, during the design process, assist the understanding and the forecast of the flow field behavior by the assessment of the aerodynamic and thermal performances of the considered blade cooling geometry.