Abstract
Despite several studies on the optimum shape of film cooling holes, only a small number of research efforts have attempted to optimize the hole arrangement for film cooling. Moreover, although the manufacturing tolerance has substantial effects on the performance of film cooling, the studies on this issue are even scarcer. The present study proposed a robust design optimization procedure that takes the manufacturing uncertainties into account; it was subsequently applied to the film holes on a high-pressure turbine nozzle to obtain a high-performance array shape that is robust to the manufacturing tolerance. To this end, the hole array was parameterized using newly suggested shape functions and two representative manufacturing factors were considered for the film holes. Additionally, Monte Carlo simulation was employed using the kriging surrogate model for a probabilistic design procedure; design optimization was performed using a genetic algorithm. As a result of the optimization, it was possible to obtain a nozzle with superior cooling performance and a robustness maximum 7.66 and 52.53% higher than that of the baseline, respectively. Additionally, it was confirmed that the tolerance of the holes near the leading edge is more influential on the cooling performance than that of the other holes.
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