Abstract
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.
Highlights
The increase thrust performance for a space-plane and a rocket is important
In order to increase the thrust of pulse detonation engine (PDE), we will conduct to design and manufacture an optimum supersonic nozzle, which is based on the characteristics method of the supersonic nozzle for single pulse detonation in the paper
In order to confirm the effectiveness of the nozzle, we compare the impulse and specific impulse with nozzle and no nozzle for methane-oxygen and hydrogen-oxygen gas mixtures through the ballistic pendulum method
Summary
The increase thrust performance for a space-plane and a rocket is important. A pulse detonation engine (PDE) was proposed on 1990s, and PDE has been studied in many institutions [1] [2]. Our final goal is to design, manufacture and operate PDE for the space and air-breathing propulsion devices at. (2014) Improvement of a Propulsion Equipment with a Supersonic Nozzle for Single Pulse Detonation. In order to increase the thrust of PDE, we will conduct to design and manufacture an optimum supersonic nozzle, which is based on the characteristics method of the supersonic nozzle for single pulse detonation in the paper. Performance of the nozzle ejector is investigated by experiment and CFD analysis to validate appropriateness of the design
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