基于射流技术的涡轮叶尖泄漏流损失控制数值研究  

Numerical research using flow injection on loss control of turbine blade tip leakage

作　　者：宋杨[1] 乔渭阳[2] SONG Yang;QIAO Wei-yang(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China;School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China)

机构地区：[1]上海飞机设计研究院,上海201210 [2]西北工业大学动力与能源学院,西安710129

出　　处：《燃气涡轮试验与研究》2017年第5期18-25,共8页Gas Turbine Experiment and Research

摘　　要：利用CFD数值模拟方法研究了GE-E^3第一级高压涡轮的端区流场。针对间隙泄漏流流场损失,采用叶尖射流的主动控制方法,分析和比较了由此对端区流场及涡轮效率的影响。结果表明:在涡轮动叶叶尖采用合适的射流孔、射流流量或射流角度,可有效提高涡轮效率;涡轮端区流场对射流孔位置变化最为敏感,射流流量次之,而射流角度变化的作用有限;采用多孔射流方案时,涡轮效率最大可提高0.7%;采用叶尖射流主动控制的最终效果,取决于射流带来的正面作用与负面影响。Based on numerical simulation,the detailed tip leakage flow structure in the first stage high-pressure turbine of GE-E3was studied.Considering the loss generated in the turbine rotor,tip clearance injection active control was adopted to analyze and compare the effects on the endwall flowfield and turbine efficiency.The results show that appropriate scheme of active control,e.g.injection holes location,injection mass flow or the circumferential angle of injection,can effectively raise the efficiency of turbine.Among these factors,the flow structure in tip clearance of turbine rotor is most sensitive to injection holes location,then mass flow and injection angle.When the project of multihole injection was investigated,the maximum increase of efficiency for turbine could achieve0.7%.The final effect of using injection in rotor tip clearance depends on both two sides it originates.

关 键 词：涡轮 叶尖泄漏流 射流 流场 主动控制 数值模拟 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]