重庆理工大学学报（自然科学版）2017，Vol.31Issue(11)：109-116,178,9.DOI:10.3969/j.issn.1674-8425(z).2017.11.016
非设计攻角对涡轮叶片叶型损失的影响特点分析
Effects of Off-Design Incidences on Turbine Blade Profile Loss
摘要
Abstract
In order to get the law of profile loss of turbine blade on off-design incidence,a numerical simulation was carried out to analyze the flow of a high-lift low-pressure turbine at five different incidences,and to get the flow parameters of blade on five different incidences.The results show that the performance of the blade is the best at the design incidence,the air flow is equable,and the distribution of velocity gradient and pressure gradient is rule.There is no obvious boundary layer separation.In negative incidences,the flow on suction surface is well but the loss is obvious on pressure surface,and the larger negative incidence,the greater loss coefficient,but the increase of the loss coefficient is not large as a whole,the loss coefficient is only O.048 when the negative incidence increases to-20°.In positive incidences,the flow on pressure surface is well but the loss is obvious on suction surface,and the loss is much greater than the pressure surface of negative incidences.When the positive incidence is 10°,its loss coefficient has reached O.141,which is far more than the loss coefficient of-20°.Therefore,it is important to keep fit margin of positive incidences in blade profile design.关键词
高负荷低压涡轮/攻角/前加载/附面层分离/叶型损失Key words
high-lift low-pressure turbine/incidences/front-loaded/boundary layer separation/profile loss分类
航空航天引用本文复制引用
张宗辰,杜皖实,付海涛,马丽萍,白涛..非设计攻角对涡轮叶片叶型损失的影响特点分析[J].重庆理工大学学报（自然科学版）,2017,31(11):109-116,178,9.基金项目
西安航空学院校级科研基金资助项目(2017KY1230) （2017KY1230）
