以某重型燃机透平第1级动静叶片为研究对象,轮缘密封为径向-斜向密封结构。采用SST湍流模型在4种轮缘密封流量下研究密封流对下游动叶片冷却特性的影响,对比分析了有无前缘气膜冷却条件下主流流动情况和通道内涡系发展过程,结果表明:轮缘密封对叶片端壁温度变化显著的区域位于从叶片前缘沿流向约40%范围内；叶身吸力面冷却效率的分布表现为沿叶高先增大后减小的趋势,冷却效率提升最大的位置在叶片吸力面从前缘至尾缘50%位置附近；有前缘气膜冷却结构时,在MFR=0.5%及以上对端壁产生显著的冷却作用。

The first stage rotor and stator of a heavy gas turbine are taken as the research object, and the rim seal is a radial-oblique seal structure. The SST Turbulence model is used to study the influence of seal flow on the cooling characteristics of downstream rotor blade under four kinds of seal flow rates. The main flow and the development process of vortex in the channel with or without leading edge film cooling are compared and analyzed. The results show that the region where the seal has a significant effect on the blade endwall temperature locates within about 40% of the flow direction from the leading edge of the blade. The distribution of cooling efficiency on the suction surface of the blade shows a trend of increasing and then decreasing along the blade height. The position where the cooling efficiency increases most is near 50% of the suction surface from the leading edge to the trailing edge. When there is a leading edge film cooling structure, a significant cooling effect on the endwall can be achieved at MFR of 0.5% or above.

国家科技重大专项(J2019-I-0003-0004)。