Aero-thermal optimization on multi-rows film cooling of a realistic marine high pressure turbine vane

Aero-thermal optimizations on multi-rows film cooling of a realistic marine high pressure turbine vane are performed in this paper. Firstly, a full three-dimensional optimization platform for film-cooled turbines, which consists of the parametric modeling, automatic mesh generation, the CFD numerical calculation and the optimization strategy is established. The design variables are selected based on the considerations of hole-to-hole interactions and invalid coverage of cooling film. Two objective functions of aerodynamic efficiency and adiabatic film cooling effectiveness are adopted to evaluate the overall performance of film-cooled turbine vane. Bothe single objective and multi-objective optimization are adopted to optimize the configurations of multi rows film cooling holes, and the Multi-Island Genetic Algorithm and The response surface approximation with the Non-dominated Sorting Genetic Algorithm (NSGA-II) are selected to conduct the optimizations. The objective of the present study is to use a numerical optimization method to find the optimal cooling structure configurations that yields better cooling performance with an acceptable aerodynamic penalty. The results show that the film cooling effectiveness of multi-objective optimization is increased by 11.4%, and average temperature of the blade surface is reduced by 75 K.