Film-cooling hole optimization and experimental validation considering the lateral pressure gradient

The flow in the turbine endwall region consists of complicated secondary structures driven by lateral pressure gradient, which heavily affects performance film cooling. In this work, film-cooling hole design optimization is performed considering existence gradient real environment. Results have shown that optimal influenced region, especially compound angle clearly different from flat plate results are further validated with experiments using pressure-sensitive paint (PSP) technique, and cooling to be improved 42.9%. This work demonstrates importance environment also can provide guidance region.