RESEARCH ON CHEMICAL REACTION ENHANCENMENT OF SUPERSONIC MIXING GAS FLOWS

*采用氢-氧两步或八步反应模型和k-epsilon或k-omega湍流模型，开发了数值程序来求解可压缩反应流动的雷诺平均Navier-Stoces方程。将该程序应用于超燃冲压发动机燃烧室的三维混合和燃烧流场。*建立了超音速燃烧风洞，在风洞中通过在试验段上游的贫燃燃烧产生高温污染空气。将温度、压力和马赫数与设计值进行了比较。*利用准分子激光和CCD摄像系统，建立了激光诱导荧光三维定量测量技术。相关燃烧器设置中的OH浓度被成功地可视化。并编制了计算平衡化学浓度的数值程序。在此基础上，开发了计算轴对称燃烧流场的数值程序，其中适当地模拟了质量扩散项。

* Numerical codes were developed to solve the Reynolds-averaged Navier-Stoces equations for compressible reactive flows using the oxygen-hydrogen two-step or eight-step reaction model, and the k-epsilon or k-omega turbulence model. The codes were applied to the three-dimensional mixing and combustion flowefields for various parameters related the the scramjet engine combustors.* Supersonic combustion wind tunnel was constructed, in which the high temperature vitiated air is generated by the lean-bum combustion upstream of the test section. The temperature, pressure and the Mach number are compared with their disigned values. Ignition at the test section was confirmed by observation.* Experiments were conducted to establish the three-dimensional quantitative measurement technique by the laser induced fluorescence using the excimer laser and CCD camera systems. OH concentration in the correlation burner setup was successfully visualized. The numerical codes to calculate the equilibrium chemeical concetration were also developed. Further, the numerical codes were developed to calulate the axi-symmetric combustion flowfield, in which the mass diffusion terms are modeled properly.