摘要
采用数值模拟方法对高涵道比发动机涡轮过渡流道设计工况和非设计工况性能进行了详细分析,得出了与实验值较吻合的计算结果。数值结果与实验数据比较表明:所选的计算模型是可靠的,能够直接用来对带整流支板的涡轮过渡流道数值模拟;可以采用较紧凑的设计而得到对高压涡轮出口条件不敏感的低损失系统。
The numerical simulation results of design point and off-design point of high bypass ratio engine-turbine transition duct function are simulate to the experimental data.The results show that：the CFD module is reliable,can predict the turbine transition duct with struct fairing directly.Testing has verified that a low loss system,which is insensitive to the high-pressure turbine exit conditions,is achievable in a relatively compact duct design.
出处
《航空计算技术》
2012年第1期24-26,31,共4页
Aeronautical Computing Technique
基金
国家自然科学基金项目资助(51076031)
