前缘冷却结构对高压涡轮导叶流动和换热的影响  

Influence of Cooling Structures at the Leading Edge on Flow and Heat Transfer Characteristics of a High Pressure Turbine Guide Vane

作　　者：殷林林 陈云 宋伟 张勇 YIN Linlin;CHEN Yun;SONG Wei;ZHANG Yong(AECC Shenyang Engine Research Institute,Shenyang,China,Post Code:110015)

机构地区：[1]中国航发沈阳发动机研究所,辽宁沈阳110015

出　　处：《热能动力工程》2024年第8期30-40,共11页Journal of Engineering for Thermal Energy and Power

基　　金：装备预研“十四五”应用创新项目(630010104-1)。

摘　　要：为获得前缘冷却结构对高压涡轮导叶流动和换热的影响,采用三维数值模拟的方法,研究前缘不同气膜孔直径及冷气腔隔板结构时高压涡轮导叶的流动换热特性。结果表明:前缘气膜孔孔径增大使冷气量增加,但需要综合考虑冷却供气腔沿程压力损失,否则容易造成前缘区域气膜逆流裕度减小和冷气出流困难;冷气腔间的隔板位置及结构对冷气腔沿程压力分布产生影响,局部打开隔板或隔板开孔可有效减小冷气沿程压力损失,提高前缘区域的逆流裕度;导叶前缘的冲击孔及绕流柱会对气膜孔逆流裕度和冷气量造成影响,在高压涡轮导叶前缘区域的冷却结构布局设计时应综合考虑。To obtain the influence of the cooling structure at the leading edge on flow and heat transfer characteristics of a high pressure turbine guide vane,a three-dimensional numerical simulation method was used to study the flow and heat transfer characteristics of high pressure turbine guide vane with different film hole diameters and cold air chamber partition structures at the leading edge.The research results indicate that an increase in the aperture of the leading edge gas film hole leads to an increase in the amount of cold air,but it is necessary to comprehensively consider the pressure loss along the cooling supply chamber,otherwise it may lead to a decrease in the margin of the leading edge gas film countercurrent and difficulties in cold air outflow.The position and structure of the partition between the cold air chambers will have an impact on the pressure distribution along the cold air chamber.By partially opening the partition or opening holes in the partition,the pressure loss along the cold air chamber can be effectively reduced,and the countercurrent margin in the leading edge area can be improved.The impact holes and flow columns at the leading edge of the guide vanes can have an impact on the countercurrent margin and cold air mass rate of the gas film hole,and it should be comprehensively considered in design of the cooling structure in the leading edge area of high pressure turbine guide vanes.

关 键 词：冷气出流 冷却结构 数值仿真 流动换热 

分 类 号：TK221[动力工程及工程热物理—动力机械及工程]