摘要
采用发动机简化模型,以求解三维N-S控制方程为基础,数值模拟了涡轮风扇发动机的进排气流场;采用分区拼接网格技术,进行民用飞机全机低速构型气动网格划分,在保证计算精度的前提下,有效减少了网格量,提高了气动数值仿真效率;通过合理划分模拟流场区域,模拟带动力低速构型的气动特性,研究了动力对全机低速气动特性的影响。
Due to do the numerical simulation of the turbofan engine inlet and exhaust process,using simplified model of engine,based on the three-dimensional N-S equation. Under the premise that ensures accuracy of calculation. For the aircraft with low speed configuration using partition splicing grid can effectively decrease the grid number and improve calculation efficiency. By reasonable dividing the flow field to simulate the low speed aerodynamic performance of aircraft and study the turbofan engine inlet and exhaust process effecting on aircraft.
作者
王荣伟
冯丽娟
WANG Rong-wei;FENG Li-juan(Commercial Aircraft Engine Co.,Ltd.AECC,Shanghai 200241,China)
出处
《航空计算技术》
2018年第4期50-52,共3页
Aeronautical Computing Technique
基金
工信部民用飞机专项科研项目资助(MJ-2013-D-08)
关键词
涡扇发动机
N-S方程
低速构型
拼接网格
turbofan engine
N-S equation
low speed configuration
partition splicing grid