<abstract xmlns="http://www.w3.org/1999/xhtml">

<p>Numerical 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.</p>
</abstract>

Numerical 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.

Numerical Study of Detonation Processes in Rotating Detonation Engine and its Propulsive Performance

Łukasiewicz Research Network – Institute of Aviation

Transactions on Aerospace Research

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Numerical studies on detonation wave propagation in rotating detonation engine and its propulsive performance with one- and multi-step chemistries of a...

Numerical Study of Detonation Processes in Rotating Detonation Engine and its Propulsive Performance

Published Online: Oct 23, 2020

Page range: 30 - 48

DOI: https://doi.org/10.2478/tar-2020-0015

Keywords
detonation wave, rotating detonation engine, propulsion, chemical kinetics, finite volume method, adaptive mesh refinement

© 2017 Copyright by Lukasiewicz Research Network – Institute of Aviation

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Numerical Study of Detonation Processes in Rotating Detonation Engine and its Propulsive Performance

Published Online: Oct 23, 2020

Page range: 30 - 48

DOI: https://doi.org/10.2478/tar-2020-0015

Keywordsdetonation wave, rotating detonation engine, propulsion, chemical kinetics, finite volume method, adaptive mesh refinement

© 2017 Copyright by Lukasiewicz Research Network – Institute of Aviation

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Keywords
detonation wave, rotating detonation engine, propulsion, chemical kinetics, finite volume method, adaptive mesh refinement