Heat Transfer and Flow in Rotating U-Shaped Cooling Passage with 45? Ribs

This paper investigates heat transfer and flow of U-shaped cooling passage with ribs in gas turbine blade by numerical methods. The Reynolds number ranges from 10000 to 40000, and there are three cooling passages with aspect ratio of 0.5, 1, 2, then the study conducts comparative analysis for a variety of programs in case of rotating. The results show that, ribs improve cooling performance of U-shaped passage significantly while obviously increase coolant flow loss. Heat transfer capability of passage wall is proportional to Reynolds number, but overall flow loss remain basically unchanged. Rotation improve first passage heat transfer clearly by Coriolis force while there is little effect on second passage, and it does not affect overall flow loss of U-shaped cooling passage.