Study of the ignition overpressure suppression technique by water addition

The main objective of this study is to gain an understanding of the mechanisms responsible for the suppression of the ignition overpressure observed when water-is injected through discrete nozzles into a rocket exhaust. A simplified launch-vehicle/launchpad configuration of relevant importance is selected for this study. This configuration is then numerically modeled using two-phase computational fluid dynamics with a representative motor startup sequence and a series of water addition configurations. The study focuses on the interaction between the ignition overpressure wave and the injected water., Chemical reactions are not included in the model; therefore, the effect of afterburning of fuel-rich exhaust is omitted in this study. A total of 11 water addition configurations were studied. The study demonstrated that ignition overpressure is strongly affected by the cooling, of the plume and the amount of obstruction restricting the expansion of the plume. Also, the study suggests the existence of an optimal water additional rate with a weak dependence on the water nozzle pressure drop.