机匣运动下不同叶顶涡轮叶栅气热性能研究  

Study on Aerothermal Performance of Turbine Cascades with Different Tip Configurations under Casing Motion

作　　者：谭杰 刘艳[1] 张敏[1] 孙浩 杨金广 Jie Tan;Yan Liu;Min Zhang;Hao Sun;Jin-guang Yang(Key Laboratory of Ocean Energy Utilization and Energy Conservation of Ministry of Education,School of Energy and Power Engineering,Dalian University of Technology)

机构地区：[1]大连理工大学,能源与动力学院,海洋能源利用与节能教育部重点实验室

出　　处：《风机技术》2022年第4期34-39,共6页Chinese Journal of Turbomachinery

基　　金：国家自然科学基金项目(No.51876021)。

摘　　要：燃气涡轮动叶叶顶结构对跨叶顶的间隙泄漏和叶顶传热性能有着重要影响。采用实验和数值模拟方法对比研究了平顶、凹槽和拓扑优化3种不同叶顶结构的涡轮叶栅气动和叶顶传热性能。实验中,采用旋转的大转盘模拟机匣平移运动。实验结果表明:在大转盘旋转条件下,相比于平顶叶栅,凹槽叶顶实验得到的平均换热系数降低了19.07%,拓扑优化叶顶下降了1.53%。数值模拟结果显示,从叶顶压力面至吸力面“上凸-下凹-上凸”的拓扑优化结构有效地减小了超音速区域,凹槽叶顶在凹槽内的流体均以亚音速流动,相比于平顶叶栅,凹槽叶顶和拓扑优化叶顶叶栅出口质量平均总压损失系数分别减少5.38%和5.44%。The blade tip of a gas turbine cascades has an important influence on the clearance leakage flow across the tip and the tip heat transfer performance.The aerodynamic and tip heat transfer performance of turbine cascade with a flat tip,a cavity tip and topological optimized tip is studied experimentally and numerically.In the experiment,a large rotating plate is used to simulate the imitate translation of the casing.Experimental results show that compared with the flat tip cascade,the averaged heat transfer coefficient of the cavity tip and the topological optimized tip are reduced by19.07%and 1.53%respectively by comparing with the flat tip cascade.The numerical results show that the topologyical optimized tip effectively reduces the size of the supersonic region by the"convex concave convex"structure from the tip pressure surface to the suction surface.The fluid in the groove of cavity tip flows at subsonic speed.Compared with the flat tip cascades,the mass-averaged total pressure loss coefficients at the outlet for the cavity tip cascades and topology optimized tip cascades are reduced by 5.38%and 5.44%respectively.

关 键 词：机匣旋转 气热性能 泄漏流 平顶 凹槽叶顶 

分 类 号：TK47[动力工程及工程热物理—动力机械及工程] V231.3[航空宇航科学与技术—航空宇航推进理论与工程]