This article presents the optimization of the design of a subscale effusion-cooled rocket engine inner liner made of porous composite material, with the aim of improving the ability of the coolant film to protect the combustion chamber wall from thermochemical attacks. The optimization problem is defined as a global minimization problem and solved using response surface methodology (RSM). Recommendations to construct an efficient D-optimal design in a constrained design domain using design of experiments theory are provided. Computational fluid dynamics simulations are carried out to provide measurements of the response. The iteratively reweighted least squares method is used in the fit of the regression models to improve the efficiency of RSM with no additional cost. Enhanced coolant film properties for the optimal design show that the optimization problem was properly solved and the inner liner design was successfully optimized. These results demonstrate the efficiency of the optimization method.

本文提出了一种由多孔复合材料制成的亚尺度射流冷却火箭发动机内衬的优化设计，旨在提高冷却剂膜保护燃烧室壁免受热化学攻击的能力。优化问题被定义为全局最小化问题，并使用响应面方法 (RSM) 解决。构建高效D的建议- 提供了使用实验设计理论在受约束的设计域中进行的优化设计。进行计算流体动力学模拟以提供响应的测量。迭代重新加权最小二乘法用于回归模型的拟合，以提高 RSM 的效率，而无需额外成本。优化设计的冷却液膜性能增强表明优化问题得到了妥善解决，内胆设计成功优化。这些结果证明了优化方法的效率。