为获得高压涡轮导叶前缘冷却结构对流动和换热的影响特性,采用三维数值仿真的方法,研究了前缘不同气膜孔大小及隔板结构的流动换热特性。研究结果表明：前缘气膜孔孔径增大带来冷气量的增加,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会对冷气腔沿程压力分布产生影响,通过局部打开隔板或者隔板开孔可以有效地减小冷气的沿程压力损失,提高前缘区域的逆流裕度；冲击孔及绕流柱会对气膜孔逆流裕度和冷气量造成影响,在冷却设计时应综合考虑。

To obtain the flow and heat transfer characteristics of the cooling structure at the leading edge of a high-pressure turbine vane, a three-dimensional numerical simulation method was used to study the flow and heat transfer characteristics of different film hole sizes and baffle 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 flow 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 hole and flow column 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.

TK

装备预研”十四五”应用创新项目