Flow visualization and supersonic combustion studies of an acoustically open strut cavity

In this study, the supersonic flow over strut cavities was experimentally studied to understand flow features. Instantaneous schlieren imaging in non-reacting flow experiments exhibited the seven types of waves associated with cavity pressure oscillations and the formation of unstable shear layers on both sides. The shear layers moved in and out in synchronous and asynchronous modes at the trailing edge of the strut cavities. The symmetrical wave structure appeared on both sides in the synchronous mode, whereas the shear layers appeared in different stages of the cavity pressure oscillation cycle in the asynchronous mode, resulting in an asymmetrical wave structure. The pressure waves generated at the trailing edge of the strut cavities perturbed the shear layers during their movement toward the leading edge, creating a wavy shear layer with alternate troughs and crests. The pressure oscillations of the strut cavities had high-amplitude cavity modes with broadband noises, and their amplitude decreased from the trailing edge to the leading edge. The estimated recovery factor using the time lag between the signals of the leading and trailing edges showed that the flow inside the strut cavities was low subsonic. The measured dominant pressure oscillation modes had a closer match with the Rossiter modes. The pressure coefficient demonstrated that fluid accumulation inside the cavity increased with an increase in the aspect ratio. Furthermore, a higher fluid mass accumulated at the trailing edge than at the leading edge, and the difference in fluid accumulation increased with an increase in the aspect ratio. Supersonic combustion experiments with strut cavities showed that the strut cavity stabilized the flame. Moreover, the addition of an acoustically open strut cavity ahead of the flame-stabilizing cavity advanced the heat release location upstream