Two-dimensional numerical simulation of magneto-hydro-dynamic augmentation of pulse detonation engines

Abstract

The technology of magnetohydrodynamic (MHD) acceleration has received significant attention due to its wide application prospect in aeronautics and astronautics. With the development of MHD acceleration, thrust of pulse detonation engines can be increased by MHD augmentation. In the pulse detonation induced MHD ejector (PDIME) concept, under-expanded flow at the exit of converging-diverging nozzle propagates upstream into the bypass tube. The seeded air stream in the bypass tube is first shocked and raises to high-temperature to ionize thermally. The magnetic field energy is appended to accelerate the ionization gas in bypass tube, thus augments the propulsive performance of PDE. In this paper, the model of gas-liquid two-phase detonation engine with bypass was established. The engine was ignited by plasma jet. Conservation Element and Solution Element (CE/SE) method was deduced to solve plasma jet ignition and detonation process with MHD accelerator. The computational results show that the deduced CE/SE method can be efficient to capture discontinuity such as the shock at the appliance of PDIME. It has been observed that thrust augmentation can be accomplished by the bypass accelerator, even the bypass accelerator will activate originally only under a given magnetic field intensity and diameter of the bypass tube. Further analysis and optimization are required to improve performance. The results have certain significant reference for the experimental study in future.