RESEARCH ON CHEMICAL REACTION ENHANCENMENT OF SUPERSONIC MIXING GAS FLOWS

点击翻译按钮获取中文摘要

* 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.