Computational Analysis of Mixing in Strut Based Combustion at Air Inlet Mach number 2

Abstract

A computational analysis of mixing of hydrogen and air has been performed considering scramjet (supersonic combustion ramjet) combustor. Hydrogen is injected at M=1 through the rear of a simple strut located at a distance of 37.54 mm from inlet of combustor. The shape of the strut is chosen in a way to produce strong streamwise vorticity and thus to enhance the hydrogen/air mixing. Strength and size of the vortices are defined by the strut geometry and may be modified. The induced vortices cause an increase in entropy and larger losses in total pressure.

Numerical simulations of single and multi-staged injection of H2 in a supersonic scramjet combustor

“…In addition, the penetration of the fuel jet may be insufficient. Wall injectors have the advantages of ease in manufacturing, simplicity in cooling, and no pressure losses if switched off in the case of staged injection [12,13].…”