涡轮大扩张过渡段的流动分离与控制数值研究

Numerical Investigation of Flow Separation and Control in Large Expanding Turbine Transitional Sect

现代高性能涡轮机械中,研究者一直在努力提高其气动性能,体现在涡轮气动参数设计上就是：每个级利用最大焓降、最小的轴向长度、最少的每排叶片数、设计工况最高的效率。这些气动设计特点使得航空涡轮低压级静叶入口段具有较大的向外扩性,给发动机内外端壁及其高低压过渡段的设计带来了难度。通过数值模拟,探讨了一种减小扩压段流动分离的型线设计方法。

In a modern turbine design, the designers always trying to improvement it＇s performance： the maximum enthalpy per stage ; the shortest axial length ; the minimum blade rows and the highest efficient in design and off design condition. To satisfy theses design characters, the meridian geometry of the engine will be excurvature at a high degree and is difficulty to design. At the present paper, a method how to control the meridional separation by using a improved cascade will be discussed.