基于后掠台阶流动的航空发动机尾锥流线型设计方法  

Streamline Design Method of Aero-engine Exhaust Cone Based on Backward-facing Step Flow

作　　者：周铮[1] 孙正中[2] 苏莫明[2] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500 [2]西北工业大学动力与能源学院,陕西西安710072

出　　处：《燃气涡轮试验与研究》2009年第4期57-60,共4页Gas Turbine Experiment and Research

摘　　要：受后掠台阶流动中旋涡形状类似于航空发动机中尾锥的启示,提出了发动机尾锥的流线型设计方法。对平面后掠台阶流场通过流线捕捉技术得到尾锥母线,该母线绕中心轴旋转所得即为流线型尾锥。通过全三维湍流数值模拟,对流线型尾锥和具有相同扩张比的圆锥形尾锥的流场进行了比较,得出了流线型尾锥在气流参数分布、流动组织上均具有优异性能的结论。Enlightened by the similarity between the shape of recirculation region in backward-facing step （BFS） and the exhaust cone in the jet engine, a streamlined exhaust cone design method is created. A streamline capture technique is employed in the plane BFS flow field to get the generatrix. Rotating the captured generatrix around the center axis then generates the streamlined exhaust cone. Comparison of the flow fields of the streamlined exhaust cone and the traditional taper cone with the same expansion ratio are conducted by three-dimensional turbulent numerical simulation, and the results show that the streamlined exhaust cone is better at both allocating the flow parameters and organizing gas flow.

关 键 词：尾锥 后掠台阶流动 流线型设计 湍流 

分 类 号：V235.133[航空宇航科学与技术—航空宇航推进理论与工程]