In order to reveal the influence of scramjet combustor regenerative cooling structure parameters on flow and heat transfer of aviation kerosene, and realize the optimization of the structure parameters under condition of the fixed total number of cooling channels, this paper researches respectively flow and heat transfer condition of No. 3 aviation kerosene in cooling channel with different inside wall thickness, fin thickness and aspect ratios taking single cooling channel as an object of study. The results show that the cooling effect is improved and the flow pressure loss increases slightly with decrease of the inside wall thickness. The cooling effect is improved and the flow pressure loss increases rapidly with increase of the fin thickness. The cooling effect deteriorates and the flow pressure loss decreases rapidly with increase of height. But the three structure parameters have little effects on the fluid temperature. In addition, the influence mechanism is theoretically analyzed respectively. On this basis, an optimal design of cooling channel is made by goal driven optimization and MOGA in Workbench for the best possible cooling effect and the smallest possible flow pressure loss. The checkout shows that the optimized structure meets the needs of the design pursuit.