Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant

A small rotating detonation engine (RDE) model and the corresponding experimental setup were constructed for the experimental investigation of the detonation propagation characteristics and thrust performance of a circular RDE. Experiments were conducted at a range of 0.3–2.5 equivalence ratio with...

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Main Authors:	Hyung-Seok Han, Eun Sung Lee, Jeong-Yeol Choi
Format:	Article
Language:	English
Published:	MDPI AG 2021-03-01
Series:	Energies
Subjects:	pressure gain combustion rotating detonation engine detonation propagation characteristics thrust performance
Online Access:	https://www.mdpi.com/1996-1073/14/5/1381

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spelling	doaj-e37fed45d16042ab83877d611b54df762021-03-04T00:02:32ZengMDPI AGEnergies1996-10732021-03-01141381138110.3390/en14051381Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> PropellantHyung-Seok Han0Eun Sung Lee1Jeong-Yeol Choi2Department of Aerospace Engineering, Pusan National University, Busan 46241, KoreaDepartment of Aerospace Engineering, Pusan National University, Busan 46241, KoreaDepartment of Aerospace Engineering, Pusan National University, Busan 46241, KoreaA small rotating detonation engine (RDE) model and the corresponding experimental setup were constructed for the experimental investigation of the detonation propagation characteristics and thrust performance of a circular RDE. Experiments were conducted at a range of 0.3–2.5 equivalence ratio with a total mass flow rate of less than 180.0 g/s using a C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> mixture. Irregularly unstable detonative combustion occurs immediately after the detonation initiation, which includes initiation, propagation, decaying, and the merging of detonation waves. Following this, periodically unsteady detonative combustion occurs in the circular channel, resulting in the stable operation of the RDE. During stable operation, two detonation waves are predominant, rotating along the wall at a speed lower than the Chapman–Jouguet (CJ) detonation speed. The characteristic velocity efficiency is approximately 73% on average. The low characteristic velocity efficiency is presumed to be caused by the unoptimized combustion channel and the poor mixing efficiency owing to the two-dimensional injector configuration. The effect of the RDE component design and the RDE flow field characteristics need to be further investigated for improving the performance of the RDE.https://www.mdpi.com/1996-1073/14/5/1381pressure gain combustionrotating detonation enginedetonation propagation characteristicsthrust performance
collection	DOAJ
language	English
format	Article
sources	DOAJ
author	Hyung-Seok Han Eun Sung Lee Jeong-Yeol Choi
spellingShingle	Hyung-Seok Han Eun Sung Lee Jeong-Yeol Choi Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> Propellant Energies pressure gain combustion rotating detonation engine detonation propagation characteristics thrust performance
author_facet	Hyung-Seok Han Eun Sung Lee Jeong-Yeol Choi
author_sort	Hyung-Seok Han
title	Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> Propellant
title_short	Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> Propellant
title_full	Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> Propellant
title_fullStr	Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> Propellant
title_full_unstemmed	Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> Propellant
title_sort	experimental investigation of detonation propagation modes and thrust performance in a small rotating detonation engine using c<sub>2</sub>h<sub>4</sub>/o<sub>2</sub> propellant
publisher	MDPI AG
series	Energies
issn	1996-1073
publishDate	2021-03-01
description	A small rotating detonation engine (RDE) model and the corresponding experimental setup were constructed for the experimental investigation of the detonation propagation characteristics and thrust performance of a circular RDE. Experiments were conducted at a range of 0.3–2.5 equivalence ratio with a total mass flow rate of less than 180.0 g/s using a C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> mixture. Irregularly unstable detonative combustion occurs immediately after the detonation initiation, which includes initiation, propagation, decaying, and the merging of detonation waves. Following this, periodically unsteady detonative combustion occurs in the circular channel, resulting in the stable operation of the RDE. During stable operation, two detonation waves are predominant, rotating along the wall at a speed lower than the Chapman–Jouguet (CJ) detonation speed. The characteristic velocity efficiency is approximately 73% on average. The low characteristic velocity efficiency is presumed to be caused by the unoptimized combustion channel and the poor mixing efficiency owing to the two-dimensional injector configuration. The effect of the RDE component design and the RDE flow field characteristics need to be further investigated for improving the performance of the RDE.
topic	pressure gain combustion rotating detonation engine detonation propagation characteristics thrust performance
url	https://www.mdpi.com/1996-1073/14/5/1381
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Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C<sub>2</sub>H<sub>4</sub>/O<sub>2</sub> Propellant

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