Affiliations: National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, Jiangsu, China
Correspondence:
[*]
Corresponding author: Chun-Sheng Weng, National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China. Tel.: +86 25 8431 5932; Fax: +86 25 8431 5644; E-mail: [email protected]
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.
