叶顶凹槽对燃气透平动叶气动性能及叶顶传热的影响  

Effects of Squealer Tip on Blade Aerodynamic Performance and Tip Heat Transfer in Gas Turbine

作　　者：杨佃亮[1] 丰镇平[1] 

机构地区：[1]西安交通大学叶轮机械研究所,西安710049

出　　处：《西安交通大学学报》2008年第5期650-650,共1页Journal of Xi'an Jiaotong University

基　　金：国家重点基础研究发展计划资助项目(2007CB210107)

摘　　要：应用数值方法研究了燃气透平动叶顶部凹槽对动叶气动性能及叶顶传热的影响，计算求解稳态可压时均N—S方程，湍流模型采用标准k-∞湍流模型，总体求解精度为二阶．计算叶型为一个典型现代燃气轮机动叶片，叶顶凹槽深度取3％相对叶高，考虑了5种不同叶顶间隙的影响．结果显示：在凹槽内存在复杂的流动结构，相对平顶部动叶，凹槽能够显著降低叶顶泄漏流量，减小泄漏损失，尤其在大间隙时更为明显；在小间隙时采用凹槽状叶顶可以降低叶顶热负荷，而在大间隙时凹槽状叶顶的热负荷反而高于平顶的热负荷．Effects of squealer tips on blade aerodynamic performances and tip heat transfer in a gas turbine were investigated.CFD simulations were performed for both flat and squealer blade tips by solving steady compressible Reynolds-averaged N-S equations in conjunction with the standard k-ω two-equation turbulence model.The overall accuracy was of the second order.The blade calculated was a typical rotor blade in a modern gas turbine.The groove depth-blade span ratio was specified as 3%.The influences of five different tip gap-blade span ratios,e.g.,0.4%,0.7%,1.0%,1.3%,and 1.6%,were considered.The results show that,by comparison with the flat tip,the squealer tip can reduce the blade tip leakage flow and increase the blade aerodynamic efficiency,especially in the case of large gap.Moreover,the heat load of the squealer tip decreases for the small gap while increases for the large gap.

关 键 词：凹槽深度 气动性能 燃气透平 动叶片 传热 湍流模型 求解精度 热负荷 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程] U664.4[交通运输工程—船舶及航道工程]