摘要
基于航空发动机红外辐射特性数值仿真的需求,建立涡扇发动机部件的几何模型,利用数值模拟结合实验验证的方法对涡轮后内外流场及壁面温度场进行研究。比较模型与常用模型的计算结果可得出:受发动机部件几何型面及安装特点影响,发动机喷管前的内部流场及壁面温度场都成明显的周期分布。壁面温度分布形态主要受波瓣混合器影响,但加力部件使高温区域面积减小,使壁面温度分布更快进入轴对称状态。加力部件降低了发动机内部的速度分布均匀度;同时也使截面参数分布更均匀。当采用环形混合器时,流向截面上流向涡尺寸大、强度小、温度掺混情况差。
The geometric model of components after low-pressure turbine of an aero-engine was established, and computational fluid dynamics numerical simulation was conducted to investigate flow field with and without flameholder respectively. Results of simulation show that under maximum thrust mode, nozzles of both models are on over expansion operation, and total pressure losses of the model with flame-holder is 1.3%, thrust losses is 1.45 % ; in the model with flame-holder the mixing effect of temperature is improved, while the mixing effect of velocity becomes worse; the mechanism for influence of flame-holder on mixing effect is that flame-holder can increase strength and coveraze of vortex in interior flow.
出处
《科学技术与工程》
北大核心
2014年第23期120-125,共6页
Science Technology and Engineering
关键词
内外流场
数值模拟
加力部件
掺混效果
涡量
flow field
numerical simulation
afterburner
mixing effect
vortex
