Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow
Numerical investigation on staged sonic jet interaction mechanism in a supersonic cross flow
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DOI：
10.1177/0954410014523744
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发表时间：
2014-02
期刊：
影响因子：
--
通讯作者：
Wei Huang
中科院分区：
文献类型：
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作者：
Wei Huang
分级喷射方案是吸气式高超声速推进系统研究的热点，燃料喷射角对燃料与超声速横流的混合效果有很大影响。采用雷诺平均Navier-Stokes方程和SST k-ω湍流模型，研究了分级喷射流场的相互作用机理，分析了喷射角、喷射角布置方式和喷射器间距对流场特性的影响。同时，采用三种网格尺度进行了网格独立性分析，并将单横向注入方案的预测结果与公开文献中的实验数据进行了比较。结果表明，喷射器间距为1 mm时的穿透高度最高，这可能是由于喷射器之间的冲击波/冲击波相互作用最强。同时，由于燃料喷射的阻塞，穿透高度随着超音速空气流向下游流动而增加，并且由第一和第三喷射器产生的波系的影响不能分别向下游和上游传播。在流量不变的情况下，多通道喷射方案比单通道喷射方案具有更好的燃料穿透性能，且具有一定角度的多通道喷射方案比分级横向喷射方案具有更高的总压恢复效率。此外，分级横向喷射流场能为燃料射流与边界层的混合提供更好的回流区，且分离长度随喷嘴间距的增大而增大。
The staged injection scheme has drawn an increasing attention for the airbreathing hypersonic propulsion system, and the fuel injection angle has a large impact on the mixing improvement between the fuel and the supersonic cross flow. The Reynolds-averaged Navier–Stokes equations associated with the SST k-ω turbulence model have been employed to investigate the interaction mechanism in the staged sonic injection flow field, and the influences of the injection angle, the injection angle arrangement, and the distance between the injectors on the flow field characteristics have been analyzed comprehensively. At the same time, three grid scales have been used to perform the grid independency analysis, and the predicted results have been compared with the experimental data in the open literature for the single transverse injection scheme. The obtained results show that the penetration height for the cases with the distance between the injectors being 1 mm is the highest in the range considered in the current study, and this may be due to the strongest shock wave/shock wave interaction between the injectors. At the same time, due to the blockage of the fuel injection, the penetration height increases as the supersonic air stream flows downstream, and the influence of the wave system generated by the first and third injectors cannot propagate downstream and upstream, respectively. The multi-port injection scheme can provide better fuel penetration performance than the single one when the flow flux keeps constant, and the multi-port injection scheme with a certain angle can provide a higher total pressure recovery efficiency than the staged transverse injection scheme. Further, the staged transverse injection flow field can provide a better recirculation zone for the mixing between the fuel jet and the boundary layer, and the separation length increases with the increase of the distance between the injectors.