Enhanced mixing in supersonic combustion

To control the reaction progress in supersonic combustors the fuel/air mixing has to be optimized which is investigated numerically in this paper. The mixing process is strongly influenced by, the design of the fuel strut injector. Optimizationstudies may help to improve the mixing efficiency of real size scramjet (supersonic combustion ramjet) engines. The strut design used in this paper is the result of previous experimental and numerical investigations [1, 2, 3]. It has been verified that the use of lobed strut injectors improves the mixing by generation of streamwise vortices in the core region of the combustion chamber. The present study compares two different nozzle exit designs using basically the same strut shape. 295 K cold hydrogen is injected with Mach 2.0 into a 1300 K hot Mach 2.0 supersonic air flow.