涡流燃烧发动机燃烧室数值模拟  

Numerical Simulation of Vortex Cold-wall Rocket Combustor

作　　者：孙得川[1] 白荣博[1] 刘上[1] 

机构地区：[1]西北工业大学固体火箭发动机燃烧热结构与内流场国防科技重点实验室,西安710072

出　　处：《弹箭与制导学报》2011年第2期111-113,116,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家863基金(2007AA0168);航天创新基金(CASC0309)资助

摘　　要：为研究涡流冷壁火箭发动机燃烧室内部的流动情况,分别采用RNGk-ε模型和雷诺应力模型对涡流冷壁发动机燃烧室流场进行数值模拟,确定采用雷诺应力模型能够较好的模拟冷态双旋涡流动。通过数值模拟得到了外层准自由涡,内层准强迫涡的Rankine组合涡结构。研究表明:数值模拟得到的流动结果比冷态模型更接近实际情况;三维效应在准自由涡区域比较明显,在强迫涡区域很小,总体上不影响燃烧室内的双旋涡流动结构。In order to study the flow field of vortex cold-wall rocket eombustor, two turbulent models were used and compared by using CFD software, RSM turbulent models can simulate the pressure distribution, swirl velocity and bidirectional vortex very well. The Rankine vortex structure was obtained through numerical simulation. The results show that the calculation results even more agree better real combustor than the theoretical model, and the 3-D effect is apparent in the free vortex but smaller in the forced vortex and will not influence the structure of bidirectional vortexes.

关 键 词：涡流冷壁推力室 双旋涡结构 数值模拟 RSM模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]