Role of Ignition Delay in Rotating Detonation Engine Performance and Operability

Stechmann, David P.; Sardeshmukh, Swanand V.; Heister, Stephen D.; Mikoshiba, Kota

doi:10.2514/1.b37117

Cited by 28 publications

(3 citation statements)

References 16 publications

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“…al compared their empirical results and thermo-chemical calculations and showed that non-adiabatic mixing of the reactants and products may need to be accounted for to better predict the pre-detonation mixture [15]. Furthermore, Stechmann et al studied the impact of product recirculation on autoignition time delays in rocket-type RDCs for different fuels [16]. Their reactor model shows that depending on the amount of mixing, the mixture may ignite on the time scales of the cycle time of the RDC.…”

Section: Introductionmentioning

confidence: 99%

Low-Order Model for Detonation Velocity Suppression in Rotating Detonation Combustors

Barnouin

Bach

Gutmark

et al. 2023

AIAA SCITECH 2023 Forum

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A Rotating Detonation Combustor (RDC) is a novel pressure gain combustion device, in which a detonation wave processes steadily around an annulus. It has been experimentally observed that detonation waves in the RDC propagate slower than the idealized Chapman-Jouguet (CJ) speed (as low as approximately 60%) and with lower than expected peak pressures. This work then attempts to develop a low-order model to identify the impact of non-ideal processes on these key detonation properties. Three mechanisms are incorporated: the buffer region created by non-premixed reactant injection, parasitic combustion of reactants, and suppression of the heat release through the detonation. While these sophisticated processes are only coarsely described by such a low-order model, it is shown that their effect results in a partial heat release that supports the detonation wave and can capture the deficit in detonation properties. One special aspect of this model is that it is designed to utilize relatively easily measured experimental data as inputs. This has the objective of providing rough, first order estimates of these more sophisticated processes than would otherwise be available by typical RDC combustor diagnostics. A parametric analysis is conducted for stable detonation runs on the RDC at TU Berlin. Convergence between predicted and experimental values show that a significant proportion of the heat release is lost in the buffer zone, undergoes parasitic combustion or is unable to contribute to the detonation heat release.

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Section: Introductionmentioning

confidence: 99%

Low-Order Model for Detonation Velocity Suppression in Rotating Detonation Combustors

Barnouin

Bach

Gutmark

et al. 2023

AIAA SCITECH 2023 Forum

View full text Add to dashboard Cite

show abstract

“…Modal transitions have been experimentally observed by Suchocki et al, Rankin et al, Stechmann et al, and Bennewitz at al. [10][11][12][13]. Figure 2 shows an example of a DMT from three to two waves captured from the RDRE exhaust plane during an experimental run [13].…”

Section: Introductionmentioning

confidence: 99%

“…However, in the case of most co-rotating DMTs, galloping detonation wave behavior intensifies until one of the waves fail becoming an uncoupled shock-deflagration, decays, and does not reinitiate (recover) [13]. Then, the subsequent deflagration wave is absorbed/merged with another detonation wave (note: in two or more RDRE wave modes) [10][11][12]. The wave interaction is a trailing detonation wave failure mode seen between 372 ms to 376 ms [13].…”

Section: Introductionmentioning

confidence: 99%

Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine

et al. 2021

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Rotating detonation rocket engines (RDREs) exhibit various unsteady phenomena, including modal transitions, that significantly affect their operation, performance and stability. The dynamics of the detonation waves are studied during a descending modal transition (DMT) where four co-rotating detonations waves decrease to three in a gaseous methane-oxygen RDRE. Detonation wave tracking is applied to capture, visualize and analyze unsteady, 3D detonation wave dynamics data within the combustion chamber of the RDRE. The mechanism of a descending modal transition is the failure of a detonation wave in the RDRE, and in this study, the failing wave is identified along with its failure time. The regions upstream of each relative detonation show the mixture and flow-field parameters that drive detonation failure. Additionally, it is shown that descending modal transitions encompass multiple phases of detonation decay and recovery with respect to RDREs. The results show high upstream pressure, heat release and temperature, coupled with insufficient propellants, lead to detonation wave failure and non-recovery of the trailing detonation wave during a descending modal transition. Finally, the Wolanski wave stability criterion regarding detonation critical reactant mixing height provides insight into detonation failure or sustainment.

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Propagation Behaviors of the Rotating Detonation Wave in Kerosene–Air Two-Phase Mixtures with Wide Equivalence Ratios

Ren

Sun

Wang

2022

Flow Turbulence Combust

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Role of Ignition Delay in Rotating Detonation Engine Performance and Operability

Cited by 28 publications

References 16 publications

Low-Order Model for Detonation Velocity Suppression in Rotating Detonation Combustors

Low-Order Model for Detonation Velocity Suppression in Rotating Detonation Combustors

Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine

Propagation Behaviors of the Rotating Detonation Wave in Kerosene–Air Two-Phase Mixtures with Wide Equivalence Ratios

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