摘要
随着涡轮进口温度的提高,采用高效气膜冷却降低叶片表面温度成为涡轮设计的主要目标之一。本文采用接近真实条件下的冷气参数,在高速风洞中进行了在叶身不同位置的冷气喷射试验,并对试验结果采用CFD软件进行了数值模拟,分析了不同冷气位置、不同冷气喷射对叶栅总损失的影响。分析了冷气喷射流场的结构,数值模拟的总体性能参数与试验结果基本一致。
With the increase of turbine inlet temperature, the technique of high efficiency film cooling to decrease the blade surface temperature has become a hot topic of turbine design. In this paper, a series of film cooled turbine cascade experiments were carried out and the influences of cooling jets＇ position on turbine cascade performance were compared. A numerical code was used to simulate the effects of cooling jets＇ position on cascade total loss. The flow field structure was analyzed through numerical simulation. The numerical results show that the total performance parameters are approximately consistent with the experimental results.
出处
《燃气涡轮试验与研究》
2008年第4期4-9,共6页
Gas Turbine Experiment and Research
