Numerical and Theoretical Study of Supersonic Turbulent Non premixed flames
The turbulent diffusion flame within the HyShot supersonic combustor was investigated using LES simulations. The LES showed that the interactions between the airstream entering the combustor and the H2 sonic jet produce an average vorticity of order 105 Hz. The interaction between the hydrogen transverse jets and the supersonic air flow leads to bow shock formation and, accordingly, to boundary layer separation. This separation allows H2 to be converted upstream through the spanwise recirculation vortices created by the baroclinic effect. Once created, the vortices are tilted, stretched, compressed and expanded according to the vorticity transport equation. These vortices are the key structures responsible for the observed fast fuel air mixing. In this context, an analysis of the flame structure is of theoretical and numerical interest. In fact, depending on this structure, a appropriate kinetic and chemical/turbulence model can be chosen to correctly predict experimental results. The flame structure has been analyzed by means of the Burke and Schumann theory.
A. Ingenito L. Romagnosi D. Cecere E. Giacomazzi C. Bruno
国际会议
上海
英文
94-103
2011-11-21（万方平台首次上网日期，不代表论文的发表时间）