Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 08, 2024 - September 11, 2024
Aviation gas turbine engines are required to be more efficient, due to consideration of environmental problems. The temperature of the combustor needs to be increased to achieve higher efficiency, and it is essential to improve the cooling performance of the high-pressure turbine. Film cooling plays a central role in high-pressure turbine cooling, and various film cooling hole configurations have been proposed. In this study, a new proposal is made to introduce a flow division promoter (FDP) into the crater hole. In the experiments, a heated wind tunnel apparatus was used at Ashikaga University. The experimental result was a bifurcation of the cooling air due to the FDP, which affected the counter rotating vortex pair (CRVP) and improved cooling performance in terms of area-averaged cooling efficiency and spanwise cooling efficiency.
