Heat transfer in rectangular channel with rib turbulators and film-cooling holes considered

We consider both rib turbulators and film-cooling holes so as to be closer to the real situation existing in gas turbine blade. We explain how to investigate such heat transfer and what we did in our investigation. The k-ω turbulence model is employed. Numerical simulation and boundary conditions were put forward. Then we give the five topics in explaining what we investigated: (1) definition of parameters; Reynolds number is 50000; suction ratios of the film-cooling holes are 0.22, 0.14, 0.09 and 0; (2) calculation of results for the case of considering only film-cooling holes; comparison of calculated results with test data; (3) the analysis of the calculated results for the case of considering only film-cooling holes; the analyses of enhanced factors of heat transfer and velocity vectors near the film-cooling hole are shown in the paper; (4) calculated results for the case of considering only rib turbulators and the analysis of these results; the analysis of enhanced factors of heat transfer is given; (5) calculated results for the case of considering both film-cooling holes and rib turbulators; the analysis of enhanced factors of heat transfer is given. On the basis of what we calculated and analyzed, we give the following two main conclusions: (1) when the rectangular channel has only rib turbulators, the separation flow in inter-rib space is the main factor in the enhancement of heat transfer; (2) when the rectangular channel has both rib turbulators and film-cooling holes, the effect of the latter on enhancing heat transfer is only secondary compared to that of the former.