Abstract
The cooling technology for the high temperature gas turbine blade is the one of the most important issues for its development. In this research the method for the heat transfer enhancement and the loss reduction of the rib turbulator and the return passage in the gas turbine blade is investigated. The combination of inclination direction of the rib turbulator for the inlet and outlet straight duct is optimized by the experiment and CFD. Using the result of the former, the rib arrangement in the returnpassage is also optimized by the experiment and CFD.
