为进一步提升重型燃气轮机单机功率与效率，需要解决透平冷却设计的技术难题。参考国际相关重型燃气轮机厂商的做法，实验筛选得到了基本柱肋冷却的构型。在此基础上，设定换热底面平均努塞尔数为优化目标，基于遗传算法进行了优化，得出了更具传热性能强化的柱肋复合构型。结果表明：相对间断型V肋而言，连续型V肋传热性能较优，但当融合连续型V肋和间断型V肋时，存在更具传热性能的柱肋构型，综合传热因子能够提高14.6% ~ 18.2%，包括一种摩擦因子较低和另一种平均努塞尔数较高的冷却通道。

In order to improving the power and efficiency of a single heavy-duty gas turbine, it is imperative to address the technical issues in turbine cooling design. Based on the practices of some international heavy-duty gas turbine manufacturers, the fundamental ribs and pin-fins cooling configuration was obtained. The average Nusselt number of the heat exchange surface was set as the optimization target, and the composite ribs and pin-fins cooling configuration with enhanced heat transfer performance was obtained through the genetic algorithm. The results indicate that the continuous V-rib exhibits superior heat transfer performance compared to the discontinuous V-rib. However, when the continuous V-rib and the discontinuous V-rib were integrated, the new configuration with even better heat transfer performance has occured, and the comprehensive heat transfer factor can be elevated by 14.6% to 18.2%, including one cooling channel with a lower friction factor and another with a higher average Nusselt number.