Author(s)

Kazuhiko Toshimitsu¹, Shuuto Mikajiri², Ryo Takahashi³

¹Department of Mechanical Engineering, Oita National College of Technology, Oita, Japan.
²Mechanical-Environmental System Engineering Major, Oita National College of Technology, Oita, Japan.
³Department of Computer Science and System Engineering, Kyushu Institute of Technology, Kitakyushu, Japan.

A pulse detonation engine (PDE) is one of candidates of aerospace engines for supersonic cruse. In the paper, a supersonic nozzle ejector is designed to increase thrust of single pulse detonation for methane-oxygen and hydrogen-oxygen mixtures. The design method is based on the conventional characteristic method and inlet condition is averaged value of detonations of methane-oxygen and hydrogen-oxygen mixtures. Comparison of thrusts with a design nozzle and no nozzle (straight- type) is conducted to ensure the designed nozzle performance. Furthermore, the flow velocity, temperature and velocity of the designed nozzle are calculated to ensure its appropriateness with the commercial software ANSYS CFX. Consequently, we succeed in increasing the thrusts of the single pulse detonation with the nozzle, which are 1.4 and 2.0 times as large as ones of straight- type for methane-oxygen and hydrogen-oxygen mixtures respectively.

Thruster, Detonation, Impulse, Supersonic Flow, Method of Characteristics, CFD, Nozzle

Toshimitsu, K. , Mikajiri, S. and Takahashi, R. (2014) Improvement of a Propulsion Equipment with a Supersonic Nozzle for Single Pulse Detonation. Open Journal of Fluid Dynamics, 4, 447-453. doi: 10.4236/ojfd.2014.45035.