Abstract
This paper focuses on the influence of ramp locations upstream of a strut-based scramjet combustor under reacting flow conditions that are numerically investigated. In contrast, a computational study is adopted using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport (SST) k-ω turbulence model. The numerical results of the Deutsches Zentrum für Luft- und Raumfahrt or German Aerospace Centre (DLR) scramjet model are validated with the reported experimental values that show compliance within the range, indicating that the adopted simulation method can be extended for other investigations as well. The performance of the ramps in the strut-based scramjet combustor is analyzed based on parameters such as wall pressures, combustion efficiency and total pressure loss at various axial locations of the combustor. From the numerical shadowgraph, more shock interactions are observed upstream of the strut injection region for the ramp cases, which decelerates the flow downstream, and additional shock reflections with less intensity are also noticed when compared with the DLR scramjet model. The shock reflection due to the ramps enhances the hydrogen distribution in the spatial direction. The ignition delay is noticed for ramp combustors due to the deceleration of flow compared to the baseline strut only scramjet combustor. However, a higher flame temperature is observed with the ramp combustor. Because more shock interactions arise from the ramps, a marginal increase in the total pressure loss is observed for ramp combustors when compared to the baseline model.
Highlights
In recent years, there has been considerable attention to the scramjet engine, which is a potential candidate for future hypersonic propulsion vehicles [1,2,3]
DLR scramjet combustorshadowgraph of identical operating conditions is discussed in thelocations subsequent
Numerical investigations on the effect of the ramp on the top and bottom wall of a strut-based scramjet combustor are compared with basic DLR strut under reacting flow conditions
Summary
There has been considerable attention to the scramjet engine, which is a potential candidate for future hypersonic propulsion vehicles [1,2,3]. The fuel injection system plays a pivotal role in enhancing the fuel–air mixing attributes and improving the overall combustion performance of the scramjet engine. A robust flame holding mechanism is needed owing to the short residence time of airflow in the scramjet combustor. There are various injection and flame holding mechanisms, such as cavities [4,5,6,7,8,9,10], pylons [11,12,13,14] and struts [15,16,17,18,19,20,21,22,23,24,25,26,27,28]. A strut-based injector configuration is among those that could solve the aforesaid issues and uphold the minimum total pressure loss
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