Optimized design on a new type thermal structure of scramjet combustor

In order to study some methods of scramjet engineering design, an active cooling thermal structure scheme based on ceramic matrix composite (CMC) is designed for scramjet combustor. Models of thermal structure design and inert mass calculation of scramjet combustor have been built up. Base on Genetic Algorithms, single-objective optimization and multi-objectives optimization have been done for thermal structure; optimized parameters include each layer thickness, trough width, rib width and rib height. According to the results of single-objective optimization, combustor mass is decreased by 21.7% and the thermal structure dimensions under minimum mass are also obtained. According to the results of multi-objectives optimization, a Pareto front is got.