Abstract
The efficient utilization of transpiration cooling is crucial for addressing coolant consumption challenges in hypersonic vehicle design. This study focuses on optimizing the blowing ratio, a key parameter in transpiration cooling. A multiobjective genetic algorithm is employed to determine the optimal blowing ratio using an experimental correlation. The optimization objectives include average thermal effectiveness, length of cooling with thermal effectiveness greater than 0.5, and coolant reservoir volume over a 60 s duration cooling process. The results reveal that a blowing ratio of 0.108 % is the optimal point, with corresponding values for average thermal effectiveness, coolant reservoir volume, and length of cooling being 0.493, 7.093 m³, and 0.14 m, respectively. A comparison with the maximum experimental blowing ratio indicates a 56.61 % reduction in average thermal effectiveness, accompanied by a 56.68 % decrease in coolant reservoir volume. This study highlights the application of multiobjective genetic algorithms in optimizing the transpiration cooling blowing ratio for hypersonic vehicles.
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