按照涡轮传热分层设计流程，对某型燃气轮机高压涡轮导叶进行了冷却结构设计。利用管网设计方法快速得到符合设计要求的基本冷却结构，采用UG建模与自编程序相结合快速生成实体模型，并选取两种典型冷却方案进行全三维气热耦合计算。计算结果表明：两种冷却方案总冷气量基本相同时，前腔冷气流量更大的方案2满足设计要求，其前腔无量纲流量为0.052 7，后腔无量纲流量为0.049 4，叶片表面无量纲平均温度为0.666 7，无量纲最大温度为0.737 1；增大吸力面“簸箕”形状气膜孔的冷气流量，可以有效降低吸力面中后部高温区域的温度；利用管网设计可以快速搜寻合理的冷却结构方案，该设计方法显著地缩短了设计周期。

According to the turbine heat transfer layer design process,the cooling structure design of a certain gas turbine highpressure turbine guide vane is carried out.To meets the design requirements,the pipenetwork design method is used to quickly obtain the basic cooling structure,and the physical models are quickly generated by the combination of UG modeling and selfprogramming,and two typical cooling schemes are selected for full 3D gasthermal coupling calculations.The calculation results show that when the total cooling air flow rate of the two cooling schemes is basically the same,the larger cool air flow rate in the front cavity of case 2 meets the design requirements.The dimensionless flow rate in the front cavity is 0.052 7,the dimensionless flow rate in the rear cavity is 0.049 4,and the dimensionless average temperature of the blade surface is 0.666 7,and the dimensionless maximum temperature is 0.737 1; the increasement of the cool air flow of the “dustpan”shaped film hole on the suction surface can effectively reduce the temperature of the hightemperature area in the middle and rear of the suction surface; the reasonable cooling structure scheme can be quickly searched by using the pipe network design,which significantly reduces the design cycle.

TK123

国家自然科学基金资助项目（52076053）