Influence of Endwall Contouring on the Secondary Flow in Turbine Nozzle Guide Vane

被引：0

作者：

孙大伟 ^{[1
]}

乔渭阳 ^{[1
]}

许开富 ^{[1
]}

机构：

[1] School of Power and Energy,Northwestern Polytechnical University

来源：

Defence Technology | 2009年 / 5卷 / 02期

关键词：

propulsion system of aviation and aerospace; endwall contouring; secondary flow; turbine nozzle guide vane;

D O I：

暂无

中图分类号：

V231.3 [航空发动机气体力学];

学科分类号：

082502 ;

摘要：

Numerical simulations are carried out to investigate the effect of the endwall contouring on the secondary flow in turbine nozzle guide vane.The three contoured cascades with the same contouring profile and the different positions where the contoured profile locates at are researched.The results show that the contouring configuration can reduce the aerodynamic losses of the cascade.The flat side takes advantage of a stronger decrease of the losses,compared to the contoured side.The contouring configuration can also inhibit the secondary flow.The contoured cascade in which the contouring profile starts upstream of the airfoil,ends at the middle of the airfoil has the best effect of improving secondary flow.

引用

页码：95 / 101

页数：7

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