The present contribution addresses the aerothermal experimental and computational study of a trapezoidal cross-section model simulating a trailing edge cooling cavity with one rib-roughened wall and slots along two opposite walls. Highly resolved heat transfer distributions for the geometry with and without ribs are achieved using a steady state liquid crystals method in part II of this paper. The reference Reynolds number defined at the entrance of the test section is set at 67,500 for all the experiments. Comparisons are made with the flow field visualizations presented in part I of this paper. The results show the dramatic impact of the flow structures on the local and global heat transfer coefficients along the cavity walls. Of particular importance is the jet deflected by the rib-roughened wall and impinging on the opposite smooth wall. The experimental results are compared with the numerical predictions obtained using the finite volume, Reynolds-Averaged Navier–Stokes solver Calcul d'Écoulements Diphasiques Réactifs pour l'Énergétique (CEDRE).
Aerothermal Investigation of a Rib-Roughened Trailing Edge Channel With Crossing Jets—Part II: Heat Transfer Analysis
Coletti, F., Armellini, A., Arts, T., and Scholtes, C. (December 7, 2010). "Aerothermal Investigation of a Rib-Roughened Trailing Edge Channel With Crossing Jets—Part II: Heat Transfer Analysis." ASME. J. Turbomach. July 2011; 133(3): 031024. https://doi.org/10.1115/1.4002425
Download citation file: