非轴对称端壁影响涡轮气动性能的数值研究  

Numerical Study of Influence of Non-Axisymmetric End Wall on the Performance of a Turbine

作　　者：张晶辉 王盼 曾瑞祥 ZHANG Jinghui;WANG Pan;ZENG Ruixiang(School of Aircraft,Xi’an Aeronautical University,Xi’an 710077,China;AVIC Xi’an Aircraft Industry(Group)Co.,Ltd.,Xi’an 710089,China)

机构地区：[1]西安航空学院飞行器学院,西安710077 [2]西安飞机工业有限责任公司,西安710089

出　　处：《兵器装备工程学报》2021年第8期159-163,共5页Journal of Ordnance Equipment Engineering

基　　金：陕西省自然科学基础研究计划项目(2021JQ-855)。

摘　　要：为提高涡轮气动性能,采用双控线造型法对设计工况下某低速涡轮平面叶栅进行数值模拟。结果表明,对涡轮叶栅下端壁采用非轴对称造型,压力梯度分布得到改善,可延缓通道涡的形成,削弱涡流强度,降低二次流损失,提高涡轮的气动性能。In order to study the effect of non-axisymmetric end wall modeling on reducing turbine secondary flow loss and improving turbine aerodynamic performance,a dual control line modeling method was used to numerically simulate a low speed turbine liner cascade under design conditions.The results show that the non-axisymmetric modeling technique of the lower end wall of the turbine cascade can improve the pressure gradient distribution,delay the formation of the passage vortex,weaken the vortex intensity,and effectively reduce the secondary flow loss and improve the aerodynamic performance of the turbine.

关 键 词：非轴对称端壁 双控线造型法 二次流损失 平面叶栅 涡轮 

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]