热力透平2025，Vol.54Issue(2)：85-90,129,7.DOI:10.13707/j.cnki.31-1922/th.2025.02.002
攻角对跨声速叶栅气动和气膜冷却特性的影响
Effects of Incidence Angle on the Aerodynamic and Film Cooling Characteristics of a Transonic Cascade
杨锐1
作者信息
- 1. 上海汽轮机厂有限公司,上海 200240||西安交通大学 能源与动力工程学院,西安 710049
- 折叠
摘要
Abstract
To further enhance the operation adaptability of the turbine cascade in various conditions,a numerical simulation model of a transonic turbine cascade with coolant flow was constructed,and the accuracy of the numerical model was validated.The influence of the mainstream incidence angle on the blade aerodynamic performance and endwall film cooling characteristics was investigated under different coolant flow masses.The results showed that with the increase of mainstream incidence angle,the transverse pressure gradient in the blade passage increased,and the transverse secondary flows and the upper and lower passage vortices were strengthened,leading to an increase in secondary flow loss.Compared with the zero-incidence-angle condition,a positive incidence angle of 4° could increase the total pressure loss coefficient by 11.8%and 11.4%respectively at mass flow ratios(MR)of 1.0%and 1.5%.Additionally,as the mainstream incidence angle increased,the lateral coverage of the coolant flow on the endwall decreased,and the mixing between the mainstream and coolant flow intensified.Consequently,larger mainstream incidence angles leaded to both smaller film cooling coverage and lower cooling efficiency on the endwall.Compared with the zero-incidence-angle condition,a positive incidence angle of 4° could reduce the area-averaged endwall film cooling effectiveness by 29.5%and 31.6%respectively at MR of 1.0%and 1.5%.The research findings can provide reference for design of endwall flow and film cooling in transonic blade cascades.关键词
端壁冷却/进口攻角/二次流/数值模拟Key words
endwall cooling/incidence angle/secondary flow/numerical simulation分类
能源与动力引用本文复制引用
杨锐..攻角对跨声速叶栅气动和气膜冷却特性的影响[J].热力透平,2025,54(2):85-90,129,7.
