可压缩修正的k-ε模型在喉部射流推力矢量喷管中的应用  

Numerical study on vector nozzle based on throat secondary injection using compressibility-modified k-ε turbulence model

作　　者：汪东[1] 刘明侯[1] 韩省思[1] 张先锋[1] 陈义良[1] 

机构地区：[1]中国科学技术大学热科学与能源工程系,安徽合肥230027

出　　处：《中国科学技术大学学报》2008年第4期405-409,共5页JUSTC

基　　金：国家自然科学基金(10372099)资助

摘　　要：对标准的k-ε双方程湍流模型进行了可压缩性修正,并数值研究二次流矢量喷管中二次流不同入射角度时,二次流入射质量比对矢量偏角、推力效率的影响.通过比较实验数据,发现可压缩修正的k-ε双方程模型较标准k-ε模型、单方程湍流模型具有更好的计算精度.数值研究结果发现,二次流在获得较大的矢量偏角同时,系统推力效率降幅较小;当二次流入射角度为150°时,系统具有最大的矢量偏角.The k-ε turbulence model with compressibility modification was proposed. Using the modified turbulent model, the performance of the secondary inject thrust vectoring nozzle was numerically studied. Compared with experimental data, the results achieved by the modified model are better than those obtained by the single equation model and the standard k-ε model. Besides, the thrust angle and system thrust ratio varying with the secondary inject weight flow ratio, and the different secondary inject angle were studied. The result indicates that the vector nozzle can obtain a large thrust vectoring angle while the system thrust ratio decreases a little bit. The system achieves the largest thrust vectoring angle when the inject angle is 150 degrees.

关 键 词：推力矢量 喉部二次射流 可压缩修正的k-ε模型 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]