摘要
在航空大涵道比涡扇发动机涡轮过渡流道优化问题的研究中,亚音速气流在其内部流动会因为扩压作用产生较强的逆压梯度,导致气流分离、边界层分离,这是过渡流道设计中的难点。为了降低过渡流道的流动损失、增大径向偏移、并改善气动性能,根据通流模型并结合一种新的优化变量参数化模型,发展出一种带整流支板的涡轮过渡流道优化方法,并应用提出的发展方法对某大涵道比涡扇发动机带整流支板涡轮过渡流道进行优化,优化后流道静压恢复系数提高,总压损失系数降低,并且流道沿程面积在出口处减小从而有效抑制了气流分离,仿真结果证明,改进的发展方法的可行性和有效性。
The intermediate turbine duct （ITD） of high - bypass - ratio turbofan engine is a divergent channel. Due to the diffusion function, the subsonic flow in ITD can generate a strong adverse pressure gradient, which may cause flow and boundary - layer separation, which makes it hard to design the ITD. To reduce the additional flow loss, increase the radial dimension and improve the aerodynamic performance of ITD, a method, combining the through- flow modle with the geometry parameterization modle, was developed for optimizing ITD with struts, and used to optimize the ITD of a certain of high bypass ratio turbofan engine. After optimizing the static pressure recover- y coefficient was increased, the totle pressure loss coefficient was decreased, and the ITD＇s on - way area was de- creased in the outlet to restrain the flow separation. It is remarkable that this method is feasible and effective.
出处
《计算机仿真》
CSCD
北大核心
2014年第2期154-159,共6页
Computer Simulation
关键词
大涵道比涡扇发动机
涡轮过渡流道
静压恢复系数
优化
High bypass ratio turbo -fan engine
Intermediate turbine duct
State pressure recovery coefficient
Optimization
