某型飞行器发动机长尾喷管两相流数值计算  

Numerical Computation on Two-phase Flow of Long Engine Tail Nozzle of a Certain Aircraft

作　　者：左艳辉[1] 赵胜海 余文锋 

机构地区：[1]海军驻南昌地区航空军事代表室,江西南昌330024 [2]中航工业洪都,江西南昌330024

出　　处：《教练机》2015年第4期62-65,共4页Trainer

摘　　要：基于FLUENT数值仿真软件,采用颗粒随机轨道模型,对某型飞行器发动机长尾喷管内两相流及长尾喷管内烧蚀机理进行了研究。针对长尾喷管烧穿现象,给出了提高长尾喷管热防护结构可靠性的方法。Based on FLUENT numerical simulation software,the particle stochastic trajectory model is used for the study on two-phase flow and ablation mechanism in the long engine tail nozzle. For the phenomenon that long tail nozzle is burnt out,the method for improvement of reliability of thermal protection structure of long tail nozzle is put forward.

关 键 词：某型飞行器发动机 长尾喷管 颗粒随机轨道模型 两相流 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]