Numerical Study of Scramjet Combustor with Tandem Dual Cavity for Nonreactive Jets

Abstract

In the past decades flame out is a major phenomenon that paves way for high fuel consumption in scramjet combustion. For enhancing mixing and flame holding characteristics, different types of cavities are introduced in a scramjet combustion chamber which can hold air for a bit and acts like an atomizer. For increasing combustion efficiency and burnout ratios recirculation is maintained by using cavity and ramp angle techniques. In this paper numerical analysis has been carried out for two dimensional non-reacting flows in the combustor of scramjet engine with tandem dual cavity that creates high turbulent kinetic energy for ensuring combustion instability. This work is an enlightened approach for predicting the flow phenomenon that induces re-circulations after implementing various tandem dual cavities with varying length to diameter ratio and ramp angle. These in turn overcome low mixing rates due to compressibility effects at high convective Mach number.