Numerical estimation of the thrust performance on a rotating detonation engine for a hydrogen–oxygen mixture

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 C2H4/O2 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.

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Front Cellular Structure and Thrust Performance on Hydrogen–Oxygen Rotating Detonation Engine

Journal of Propulsion and Power ◽

10.2514/1.b36095 ◽

2017 ◽

Vol 33 (1) ◽

pp. 100-111 ◽

Cited By ~ 18

Author(s):

Nobuyuki Tsuboi ◽

Seiichiro Eto ◽

A. Koichi Hayashi ◽

Takayuki Kojima

Keyword(s):

Cellular Structure ◽

Rotating Detonation Engine ◽

Detonation Engine ◽

Rotating Detonation ◽

Thrust Performance

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102 Thrust Performance Evaluation on Rotating Detonation Engine by Using Numerical Simulation : Effect of Combustor Size and Number of Detonation Waves

The Proceedings of Conference of Kyushu Branch ◽

10.1299/jsmekyushu.2014.67._102-1_ ◽

2014 ◽

Vol 2014.67 (0) ◽

pp. _102-1_-_102-2_

Author(s):

Takaya Harano ◽

Yusuke Watanabe ◽

Nobuyuki Tsuboi ◽

Takayuki Kojima ◽

Koichi Hayashi

Keyword(s):

Numerical Simulation ◽

Performance Evaluation ◽

Detonation Waves ◽

Rotating Detonation Engine ◽

Detonation Engine ◽

Rotating Detonation ◽

Thrust Performance

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Three-dimensional numerical thrust performance analysis of hydrogen fuel mixture rotating detonation engine with aerospike nozzle

Proceedings of the Combustion Institute ◽

10.1016/j.proci.2018.09.024 ◽

2019 ◽

Vol 37 (3) ◽

pp. 3443-3451 ◽

Cited By ~ 13

Author(s):

Nicolas Jourdaine ◽

Nobuyuki Tsuboi ◽

Kohei Ozawa ◽

Takayuki Kojima ◽

A. Koichi Hayashi

Keyword(s):

Performance Analysis ◽

Three Dimensional ◽

Fuel Mixture ◽

Hydrogen Fuel ◽

Rotating Detonation Engine ◽

Detonation Engine ◽

Aerospike Nozzle ◽

Rotating Detonation ◽

Thrust Performance

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Numerical Modeling of the RDE

Transactions on Aerospace Research ◽

10.2478/tar-2020-0019 ◽

2020 ◽

Vol 0 (0) ◽

Author(s):

Michal Folusiak ◽

Karol Swiderski ◽

Piotr Wolański

Keyword(s):

Combustion Chamber ◽

Turbine Engine ◽

Rotating Detonation Engine ◽

University Of Technology ◽

Detonation Combustion ◽

Detonation Engine ◽

Innovative Economy ◽

Turboshaft Engine ◽

The University ◽

Rotating Detonation

AbstractThe idea of using the phenomenon of rotating detonation to propulsion has its roots in fifties of the last century in works of Adamson et al. and Nicholls et al. at the University of Michigan. The idea was recently reinvented and experimental research and numerical simulations on the Rotating Detonation Engine (RDE) are carried in numerous institutions worldwide, in Poland at Warsaw University of Technology (WUT) since 2004. Over the period 2010-2014 WUT and Institute of Aviation (IOA) jointly implemented the project under the Innovative Economy Operational Programme entitled ‘Turbine engine with detonation combustion chamber’. The goal of the project was to replace the combustion chamber of turboshaft engine GTD-350 with the annular detonation chamber.This paper is focused on investigation of the influence of a geometry and flow conditions on the structure and propagation stability of the rotating detonation wave. Presented results are in majority an outcome of the aforementioned programme, in particular authors’ works on the development of the in-house code REFLOPS USG and its application to simulation of the rotating detonation propagation in the RDE.

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