Quasi-Two-Dimensional Simulation of a Rotating Detonation Engine Combustor and Injector
Abstract
A numerical simulation of an annular rotating detonation engine with stoichiometric hydrogen-oxygen is performed. A generic, well posed, and easily implemented approach using a quasi-two-dimensional method to model the area variations through the rotating detonation engine's injector and combustor is presented. The detonation--injector interaction is studied for the case with a ratio of four between the combustor and injector's throat areas. A shock wave is formed in the divergent portion of the injector due the high back pressure created by the detonation in the combustor. A Favre-averaged steady-state analysis of stream lines and particle paths reveals that the shock causes an irrecoverable loss of stagnation pressure. Stagnation pressure gain in the combustor is insufficient to make up for the loss and the flow leaves the engine with lower stagnation pressure than in the plenum.
Versions
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BibTeX
@misc{lauchapdelaine2026quasitwodimensional,
title = {{Quasi-Two-Dimensional Simulation of a Rotating Detonation Engine Combustor and Injector}},
author = {S. She-Ming Lau-Chapdelaine and Matei I. Radulescu and Zekai Hong},
howpublished = {arXiv},
year = {2026},
month = sep,
doi = {10.48550/arxiv.2609.04519},
eprint = {2609.04519},
archivePrefix = {arXiv},
url = {https://arxiv.org/abs/2609.04519},
}
RIS
TY - UNPB
TI - Quasi-Two-Dimensional Simulation of a Rotating Detonation Engine Combustor and Injector
AU - S. She-Ming Lau-Chapdelaine
AU - Matei I. Radulescu
AU - Zekai Hong
PY - 2026
DA - 2026/09/03
PB - arXiv
DO - 10.48550/arxiv.2609.04519
UR - https://arxiv.org/abs/2609.04519
AB - A numerical simulation of an annular rotating detonation engine with stoichiometric hydrogen-oxygen is performed. A generic, well posed, and easily implemented approach using a quasi-two-dimensional method to model the area variations through the rotating detonation engine's injector and combustor is presented. The detonation--injector interaction is studied for the case with a ratio of four between the combustor and injector's throat areas. A shock wave is formed in the divergent portion of the injector due the high back pressure created by the detonation in the combustor. A Favre-averaged steady-state analysis of stream lines and particle paths reveals that the shock causes an irrecoverable loss of stagnation pressure. Stagnation pressure gain in the combustor is insufficient to make up for the loss and the flow leaves the engine with lower stagnation pressure than in the plenum.
ER -