Experimental and numerical study of the rotating detonation engine in hydrogen-air mixtures

AbstractNumerical studies on detonation wave propagation in rotating detonation engine and its propulsive performance with one- and multi-step chemistries of a hydrogen-based mixture are presented. The computational codes were developed based on the three-dimensional Euler equations coupled with source terms that incorporate high-temperature chemical reactions. The governing equations were discretized using Roe scheme-based finite volume method for spatial terms and second-order Runge-Kutta method for temporal terms. One-dimensional detonation simulations with one- and multi-step chemistries of a hydrogen-air mixture were performed to verify the computational codes and chemical mechanisms. In two-dimensional simulations, detonation waves rotating in a rectangular chamber were investigated to understand its flowfield characteristics, where the detailed flowfield structure observed in the experiments was successfully captured. Three-dimensional simulations of two-waved rotating detonation engine with an annular chamber were performed to evaluate its propulsive performance in the form of thrust and specific impulse. It was shown that rotating detonation engine produced constant thrust after the flowfield in the chamber was stabilized, which is a major difference from pulse detonation engine that generates repetitive and intermittent thrust.

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Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle

International Journal of Turbo and Jet Engines ◽

10.1515/tjj-2015-0052 ◽

2017 ◽

Vol 34 (1) ◽

Author(s):

Songbai Yao ◽

Xinmeng Tang ◽

Jianping Wang

Keyword(s):

Laval Nozzle ◽

Numerical Study ◽

Specific Impulse ◽

Three Dimensional ◽

Propulsive Performance ◽

Rotating Detonation Engine ◽

Detonation Engine ◽

One Step ◽

Rotating Detonation ◽

Three Dimensional Simulations

AbstractThe aim of the present paper is to investigate the propulsive performance of the hollow rotating detonation engine (RDE) with a Laval nozzle. Three-dimensional simulations are carried out with a one-step Arrhenius chemistry model. The Laval nozzle is found to improve the propulsive performance of hollow RDE in all respects. The thrust and fuel-based specific impulse are increased up to 12.60 kN and 7484.40 s, respectively, from 6.46 kN and 6720.48 s. Meanwhile, the total mass flow rate increases from 3.63 kg/s to 6.68 kg/s. Overall, the Laval nozzle significantly improves the propulsive performance of the hollow RDE and makes it a promising model among detonation engines.

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Numerical Study on JP-10/Air Detonation and Rotating Detonation Engine

AIAA Journal ◽

10.2514/1.j058167 ◽

2020 ◽

Vol 58 (12) ◽

pp. 5078-5094 ◽

Cited By ~ 2

Author(s):

A. Koichi Hayashi ◽

Nobuyuki Tsuboi ◽

Edyta Dzieminska

Keyword(s):

Numerical Study ◽

Rotating Detonation Engine ◽

Detonation Engine ◽

Rotating Detonation

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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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