| Citation: | YANG Hongtao, YOU Guangfei, XU Liang, et al. Multi-objective optimization design of supersonic wind-tunnel nozzle cooling structure[J]. Journal of Aerospace Power, 2023, 38（5）：1047-1057 doi: 10.13224/j.cnki.jasp.20210590
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A cooling structure for nozzle of a wind tunnel was proposed, that is: 24 channels were set on walls of anterior and posterior segments of the nozzle while staggered pin-fin structure was set on wall of nozzle throat area. The numerical simulation method of the conjugated heat transfer-structural thermal analysis was used to calculate and analyze the fluid flow, heat transfer, and stiffness performances of the overall nozzle structure. The calculation results showed that under the cooling water mass flow rate of 1 kg/s, the averaged cooling efficiency of the proposed cooling structure of the conceptual nozzle was 0.68% higher than that of the basic structure, and equivalent elastic strain of throat area of the nozzle was reduced by around 5%. The response surface model approximation method and multi island genetic algorithm were used to perform multi-objective optimization calculation of the conceptual nozzle. The results showed that the maximum wall temperature of the optimized structure was about 1.6 K lower than that of the conceptual one under the cooling water mass flow rate of 2.142 9 kg/s, and equivalent elastic strain of throat area of the nozzle was reduced by around 10%. The cooling structure design of the nozzle and its multi-objective optimization method may provide a reference for an effective thermal protection design of nozzle of wind tunnel.
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