摘要
求解了某型航空发动机的低压涡轮导向器内流场。采用的数值方法为具有 TVD性质的三阶精度GODU NOV格式 ,湍流模型为 B-L代数模型及 MML模型的混合修正模型。该涡轮导向器的一个显著特点是由于结构上的要求 ,静叶前子午流道在上端壁具有较大的扩张角。通过数值模拟及流场内涡系结构和损失的分析表明 ,由于子午扩张造成端壁附面层增厚并在静叶前形成较大的分离区。该分离区的存在不但使静叶前损失急剧增加而且使上端壁马蹄涡和通道涡尺度加大 ,强度增强 ,引起流道内损失增加。
The flow field in low pressure turbine guide vane was simulated by third order accuracy Godunov scheme with TVD property.The turbulence model was the combination of B-L algebraic model and MML model.A feature of this guide vane was existence of a long inlet duct with big meridional divergent angle in order to fulfill the requirements of the structure.The numerical simulation and analysis of the vortex structure in flow field indicated that a large separated zone resulted from the divergence of meridional profile.The separated zone not only increased loss before the stator but also increased the size and strength of horseshoe vortex and passage vortex.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2000年第4期353-356,共4页
Journal of Aerospace Power
基金
国家自然科学基金资助项目(59636180)
