Abstract: Cooling passages transition section is a kind of complex surface feature in
aero-engine turbine blade. Through feature analysis of cooling passages transition section, an
effective modeling method is proposed, which is proved to obtain the smooth transition of cooling
passages with G1 continuity. The main parameters are determined as well. Eventually the
parametric design of cooling passages transition section is realized via programming, which
achieves rapid modeling and modification of the feature. Meanwhile, it provides some good
references to the parametric design of other complex features in turbine blade.

Key words: computer application, parametric modeling, feature analysis, cooling passages
transition section