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http://www.scirp.org/journal/PaperInformation.aspx?PaperID=52856#.VKs-gMnQrzE
Author(s)
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.
KEYWORDS
Cite this paper
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.
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