湍流模型在单／双缝引射矢量喷管中的验证分析研究  

Comparative and validation study of turbulence models for fluidic thrust vectoring nozzle with multiple injection ports

作　　者：张强[1] 杨永[1] 

机构地区：[1]西北工业大学翼型、叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《空气动力学学报》2012年第5期668-674,共7页Acta Aerodynamica Sinica

基　　金：国家自然基金项目(11002117)

摘　　要：利用数值模拟方法,分别求解以SA、SSTk-ω、EASMk-ω或k-ζ湍流模型封闭的RANS方程,针对单/双缝引射的激波控制射流推力矢量喷管展开研究,在多个主喷流压比NPR(4.6,7.0,8.78,10.0)和次主流压比SPR(0.7,1.0)下,系统考察了四种不同湍流模型对射流推力矢量喷管内外流场的流场结构,性能参数及主喷管内壁面压力分布的预测能力,探讨了由激波控制产生的推力矢量随不同参数的变化规律。数值计算结果表明,四种湍流模型都能比较准确地预测出射流推力矢量喷管的性能参数和喷管流场结构,双缝引射的推力矢量效率并不一定优于单缝引射。A computational study was conducted to validate different turbulence models for fluidic thrust vectoring of a two-dimensional convergent-divergent nozzle with multiple injection ports. One of SA, SST k-ω, EASM k-ω, k-ξ model was used to close the RANS equations and then simulated both the external and internal flow of the thrust vectoring nozzle at free stream Mach number 0.05 or 0.1 with nozzle pressure ratio （NPR） from 4.6 to 10 and secondary pressure ratio （SPR） O. 7 or 1.0. All the four turbulence models had done a good job in predicting the performance of the thrust vectoring nozzle compared to the experimental data, but in the separated region there was some difference in the pressure distribution along the primary nozzle wall, it maybe caused by the unsteady effect of the separated flow. The numerical results of four turbulence models indicate that at NPR=4.6, multiple-injection nozzle has a higher efficiency of thrust vectoring, but at higher NPR, one-injection port nozzle is more efficient.

关 键 词：湍流模型 RANS 射流推力矢量 分离流 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]