流体注入的轴对称矢量喷管三维流场计算

Computation of three dimensional nozzle flow field with fluidic injection

采用Roe通量差分分裂格式对基于流体注入控制的轴对称矢量喷管内流场进行了数值模拟。流体注入的位置分别为前孔和后孔,注气压强比为0.75～2.0,注气流量比为2.5％～10.0％,矢量角变化范围为2.8°～7.8°。计算结果表明:随着注气流量和注气压强增加,流体注入所产生的喷管矢量角相应增加;注气位置对喷管矢量角影响较大,注气位置靠近喷管尾沿(后孔注气)比注气位置靠近喷管喉部(前孔注气)所产生的矢量角明显增大。

The Reynolds-averaged Navier-Stokes equations were solved numerically by Roe's flux difference splitting scheme for three dimensional nozzle flow field with fluidic injection. The location of injector slot was at ahead slot or at behind slot. Ratio of injection pressurer was 0.75 - 2.0, ratio of injection flux was 2.5% - 10.0% , and the thrust vector angle ranged from 2.8 to 7.8. The results indicate that as the ratio of injection pressure and the ratio of injection flux increases, the thrust vector angle also increases . The location of injector slot has significant effects on the predicted thrust vector angle, and the behind slot injection can produce greater thrust vector angle than the ahead slot injection. The use of fluidic injection control clearly has significant potential to meet the challenges of aircraft thrust-vectoring technology.