叶顶吸力面肋条对压气机叶栅性能的影响  

Effects of Suction Side Squealer Tip on the Performance of a Compressor Cascade

作　　者：张军[1] 马宏伟[2] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500 [2]北京航空航天大学,北京100191

出　　处：《燃气涡轮试验与研究》2014年第3期6-11,21,共7页Gas Turbine Experiment and Research

摘　　要：研究了压气机叶片顶部加吸力面肋条对压气机叶栅气动性能的影响。对叶片顶部肋条不同高度情况进行的数值模拟结果表明,在叶片顶部加肋条会导致泄漏流量变大,间隙内部损失变小,肋条对应的负荷高于基准叶片,对应的叶栅扩压能力增强;肋条越高,扩压能力越强。在压气机平面叶栅上进行的相应实验表明,叶顶吸力面肋条对应的泄漏涡周向范围、出口气流角和扩压能力都略大于基准情况,但同时出口流量平均总压损失相比基准有所增加,这与数值模拟得到的趋势基本相同。The effects of suction side squealer （ssq） tip on the flow field of a compressor cascade were inves-tigated. Ssq tip with different heights were simulated. It shows that the mass of leakage flow of the ssq tip is greater and the tip gap loss is lower. The blade loading near the tip is greater than that of the baseline which leads to greater pressure rise of the cascade. The higher the ssq gets, the greater pressure rise will be. Tests on compressor cascade also show that the coverage, outlet flow angle and pressure rise of leakage vortex are greater than those of baseline. Meanwhile the average total pressure loss of outlet flow is more than that of baseline which is the same to the trend obtained by numerical simulation.

关 键 词：压气机叶栅 吸力面肋条 泄漏流 损失 性能 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]