航空发动机燃烧室过渡态温度场的数值研究  

Numerical simulation of the temperature field in transition condition of an aero-engine combustor

作　　者：吉倩[1] 赵晨光[1] 张宝诚[1] 郭艳龙[2] 

机构地区：[1]沈阳航空工业学院,辽宁沈阳110136 [2]中国航空动力机械研究所,湖南株洲412002

出　　处：《沈阳航空工业学院学报》2010年第2期24-28,共5页Journal of Shenyang Institute of Aeronautical Engineering

摘　　要：采用FLUENT软件对某型机燃烧室在慢车、最大、巡航、最大连续状态进行三维、两相、湍流燃烧的数值模拟,获得了速度场、温度场的数值。应用该型机不同加速过程的时间较充分研究了燃烧室过渡态温度场的特性及温升速率的变化特点。By means of commercial software FLUENT,the velocity field,the temperature field and the droplet track in aero-engine combustor under the 3D two phase turbulent combustion condition for the ground idling,the peak,the cruise,and maximum continuous are numerical simulated and calculated.By the use of the times for different acceleration processes,the temperature field characters of transition condition and the increasing rate of temperature are well investigated.

关 键 词：燃烧室 过渡态 温度场 数值模拟 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]