Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor: Part I: Shock-tunnel experiments

Abstract

A series of experiments is performed in the High Enthalpy ShockTunnel Göttingen to investigate the response of the HyShotII scramjet combustor to equivalence ratios close to the critical value at which the onset of thermal choking occurs. This critical equivalence ratio is first identified (for simulated Mach-8, 27-km altitude conditions) as 0.38-0.39. Subsequent experiments cover the range between this value and 0.50. As the HyShotII combustor has a constant-area cross section, the expected behavior in this equivalence-ratio range is the formation and upstream propagation of an unsteady shock train, that would eventually lead to inlet unstart. Instead, however, the shock train is observed to become lodged in the in the heat-release zone of the combustion chamber, with a quasi-stable position that shifts upstream within creasing equivalence ratio. This behavior is distinct from the steady isolator shock train is observed to become lodged in the heat-release zone of the combustion chamber, with a quasi-stable position that shifts upstream with increasing equivalence ratio. This behavior is distinct from the steady isolator shock trains seen in traditional dual-mode scramjet configurations. The shock-train development in the present experiments is characterized through fast-response surface pressure and heat-flux measurements, as well as simultaneous high-speed schlieren and OH*chemiluminescence visualization. Possible explanations for this unexpected behavior are proposed in terms of the increased heat-transfer to the combustor walls and a possible increased uniformity of the heat release across the combustor cross-section caused by the presence of the shock train.