不同湍流模型在射流推力矢量喷管数值模拟中的比较分析研究  

Some Comparative Study of Turbulence Models for Fluidic Thrust Vectoring Nozzle

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：《西北工业大学学报》2012年第1期62-67,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(11002117)资助

摘　　要：利用数值模拟手段,分别求解以SA、SST k-ω、EASM k-ω或k-ζ湍流模型封闭的RANS方程,针对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性能参数及主喷管内壁面压力分布的预测能力,探讨了激波控制产生推力矢量随不同参数的变化规律。并基于数值分析,定量给出了二次射流所带来的主喷管性能损失。数值计算结果表明,四种湍流模型都能比较准确预测出射流推力矢量喷管的性能参数,在激波捕捉和压力预测方面,相对而言SST k-ω模型最为准确。Aim. A comparative study of computational results was conducted to investigate the capabilities of different turbulence models for the fluidic thrust vectoring of a two-dimensional convergent-divergent nozzle with one injection port. Sections 1 through 5 explain our comparative study; we present all our simulation results in Figs. 3 through 11 and analyze them. SA, SST k-ω, EASM k-ω, k-ζ models were used respectively to close the Reynolds Averaged Navier Stokes（RANS） equations and then to simulate both external and intemal flows of the fluidic thrust vectoring nozzle at free stream Mach number 0. 05, whose nozzle pressure ratio （NPR） is from 4. 6 to 10 and whose secondary pressure ratio （SPR） is 0. 7 or 1.0. Our simulation results and their analysis show that ： （ 1 ） all the four turbulence models did a good job in predicting the performance of the thrust vectoring nozzle compared with the experimental data available in the literature; （2） in the separated region, there was some difference in the pressure distribution along the primary nozzle wall; numerical results indicate that the SST k-ω model is the best, and then EASM k-ω, k-ζ model, the worst is SA model in comparison; （3） the penalty caused by the secondary injection flow was also investigated using the numerical results; as expected, it is acceptable with an adaptive thrust vector angle. Section 6 gives five preliminary conclusions in fairly good detail.

关 键 词：湍流模型 RANS 射流推力矢量 矢量效率 

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]