Ribbed channel flow is adopted for internal cooling of a 1300°C class gas turbine first stage rotor blade. Heat transfer characteristics of transverse ribbed channel flow were examined using LES (Large Eddy Simulations) and by experiments. The flow was examined over the range of Reynolds number around 10~5 that are closer to the actual engine conditions. Computational results agreed reasonably well with experimental results. Heat transfer enhancement mechanism in a ribbed channel flow was shown to be caused by advecting eddy structure and interference of a rib.
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