关键词: 再生冷却；传热分析；Box-Behnken试验设计；响应面；优化

Abstract: To lower the wall temperature of liquid rocket thruster chamber and reduce the cooling channel pressure loss，the optimization design was carried out for the parameters of the regenerative-cooled channel. The height，width，channel number of the regenerative-cooled channel and the inner wall thickness of the thrust chamber were determined as design variables; the average and the highest wall temperature of thruster chamber and the coolant pressure loss were chosen as objective functions; Box-Behnken design was adopted to get sample points that can be used to establish regenerative cooling channel model and then the objective function of the second order response surface of design variable was obtained by analyzing heat transfer program and making various schemes. The optimal results were calculated by gradient projection method，active set method and genetic algorithm. Meanwhile，the model accuracy was improved by using stepwise regression and renewing sample points at each step optimization. Calculation results show that the response surface model established in this paper precisely reflect the relationship between design variables and objective functions at lower calculation cost; there are a best aspect ratio and the number of channel that can make the optimal heat transfer characteristics in cooling channel. For two different kinds of design schemes，the objective function values at most can be reduced by 13.5% and 23.5% as compared with the initial design; the values of objective functions calculated by genetic algorithm are lower than those of gradient projection method and active set method.

Key words: Regenerative-cooling；Thermal analysis；Box-Behnken design；Response surface；Optimization