高压涡轮采用非轴对称端壁的研究  

Research of Non-axisymmetric Endwall Application on High Pressure Turbine

作　　者：温风波[1] 崔涛[1] 刘轶[1] 罗磊[1] 王松涛[1] 

机构地区：[1]哈尔滨工业大学发动机气体动力研究中心,黑龙江哈尔滨150001

出　　处：《节能技术》2012年第6期489-492,共4页Energy Conservation Technology

摘　　要：以某型高压涡轮第二级静叶为研究对象,对四种非轴对称端壁造型状况下涡轮叶栅的流动状况进行数值模拟,研究非轴对称端壁造型技术在高压涡轮中对流动产生的影响。将非轴对称端壁与轴对称端壁的计算结果对比分析,结果表明:在该型涡轮设计工况下,非轴对称端壁的应用可以明显减弱端壁处的横向压力梯度,降低出口截面处的绝对螺旋度,减少主流与二次流之间的掺混,同时使得出口气流角沿叶高分布更加均匀,改善下游动叶入口的气动条件。Based on the second stator of a certain type of aeroengine high pressure turbine,the cascade flow status with four kinds of non-axisymmetric endwall was investigated through numerical computation.The computational results between non-axisymmetric endwall and axisymmetric endwall were compared,which shows that the application of non-axisymmetric endwall profiling could reduce the transverse pressure gradient significantly at design condition.Using non-axisymmetric endwall on high pressure turbine also contributes to achieving lower absolute helicity at outlet,decreasing the mix of main flow and second flow.In addition,the outlet flow angle is well-distributed along spanwise,which improves inlet aerodynamics condition to dounstream.

关 键 词：非轴对称端壁 气冷涡轮 二次流 螺旋度 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]