射流角度对固定几何结构二元喷管气动喉道的影响  

Effect of Jet Angle on the Pneumatic Throat of 2-D Vectoring Nozzle

作　　者：郭飞飞[1] 王如根[1] 夏钦斌[1] 李勇[1] 马彩东[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038

出　　处：《空军工程大学学报（自然科学版）》2010年第3期26-29,共4页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：APTD计划资助项目(APTD-1504-04-07)

摘　　要：采用基于雷诺平均的二维N-S方程和RNGκ-ε湍流模型的有限体积法,对在喷管喉道附近注入不同角度对称射流的二元矢量喷管全流场进行了数值研究。结果表明:射流与主流的总压比RSP越大,射流角度越接近0,°喷管有效喉道面积比越小。与无射流时相比,当射流缝处于喉道处,射流缝宽度为1 mm,射流角度为0,°RSP=1.0时,喷管相对喉道面积比可达到78.15%;保持RSP不变时,改变射流角度,喷管总压恢复系数、推力系数和射流流量基本保持不变;通过改变射流角度可以有效控制喷管的喉道面积。Flow fields of 2-D vectoring nozzle at different jet angles are calculated by the finite volume method based on 2-D Reynolds average N-S equation and RNG κ-ε turbulent model.The results show that the effective throat area of the nozzle is reduced as the jet angle is closed to 0°.Compared with the case without jet,the relative throat area ratio of the nozzle can achieve 78.15% in the case of the jet location 29.5,width 1 mm,angle 0° and RSP=1.0.If RSP is kept unchanged,the coefficient of the total pressure recovery,thrust coefficient of the nozzle and the jet mass flow will approximately keep in a same level at different jet angles.The throat area of the nozzle can be effectively controlled by changing the jet angle.

关 键 词：推力矢量 二元矢量喷管 气动喉道 射流 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]