Numerical investigation of operational performance in a methane-oxygen rotating detonation rocket engine

Lietz, Christopher; Ross, Mathias; Desai, Yogin; Hargus, William A.

doi:10.2514/6.2020-0687

Cited by 23 publications

(11 citation statements)

References 17 publications

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“…The complexity of RDRE physics creates challenges to comprehensively validate every scalar field tracked by the simulation. Nevertheless, this AHFM setup has previously been shown to adequately predict chamber pressures and detonation mode parameters such as the numbers of detonation waves and wave speeds for a variety of flow conditions compared to experiments [37,38]. However, it should be noted the code does exhibit the standard simulation overprediction of engine performance metrics, such as thrust and specific impulse [37,38].…”

Section: Injection Recovery: Modeling and Simulationmentioning

confidence: 99%

“…Nevertheless, this AHFM setup has previously been shown to adequately predict chamber pressures and detonation mode parameters such as the numbers of detonation waves and wave speeds for a variety of flow conditions compared to experiments [37,38]. However, it should be noted the code does exhibit the standard simulation overprediction of engine performance metrics, such as thrust and specific impulse [37,38]. The two simulations used for the current analysis are also the subject of another recent study [39], which focuses on experimental comparison and further simulation validation for these specific cases.…”

Section: Injection Recovery: Modeling and Simulationmentioning

confidence: 99%

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Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths

et al. 2021

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A rotating detonation rocket engine (RDRE) with various convergent nozzles and chamber lengths is investigated. Three hundred hot-fire tests are performed using methane and oxygen ranging from equivalence ratio equaling 0.5–2.5 and total propellant flow up to 0.680 kg/s. For the full-length (76.2 mm) chamber study, three nozzles at contraction ratios ϵc = 1.23, 1.62 and 2.40 are tested. Detonation is exhibited for each geometry at equivalent conditions, with only fuel-rich operability slightly increased for the ϵc = 1.62 and 2.40 nozzles. Despite this, counter-propagation, i.e., opposing wave sets, becomes prevalent with increasing constriction. This is accompanied by higher number of waves, lower wave speed Uwv and higher unsteadiness. Therefore, the most constricted nozzle always has the lowest Uwv. In contrast, engine performance increases with constriction, where thrust and specific impulse linearly increase with ϵc for equivalent conditions, with a 27% maximum increase. Additionally, two half-length (38.1 mm) chambers are studied including a straight chamber and ϵc = 2.40 nozzle; these shortened geometries show equal performance to their longer equivalent. Furthermore, the existence of counter-propagation is minimized. Accompanying high-fidelity simulations and injection recovery analyses describe underlying injection physics driving chamber wave dynamics, suggesting the physical throat/injector interaction influences counter-propagation.

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Section: Injection Recovery: Modeling and Simulationmentioning

confidence: 99%

Section: Injection Recovery: Modeling and Simulationmentioning

confidence: 99%

Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths

et al. 2021

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“…Numerous mathematical models and numerical studies have been performed to capture the small-scale physics of various types of RDEs [17]. In this study, numerical data is generated using an implicit, large-eddy simulation (LES) [8]. The LES solver is a commercial product named AHFM (ALREST High-Fidelity Modeling) derived from LESLIE (LES with Linear Eddy model).…”

Section: Numerical Solver Overviewmentioning

confidence: 99%

“…Detonation waves will disappear, re-appear, merge and change direction until a particular number of detonations becomes prevalent. Once an unchanging number and direction of detonation waves develop within the RDRE, it is considered to have reached a steady operational mode [8]. Time scales commonly observed in gaseous methane-oxygen RDRE simulation start-ups are on the order of: 0.25 ms to 0.30 ms from ignition to DDT, 1.0 ms to 2.0 ms for unsteady counter-propagating to co-rotating detonation transition, and 2.0 ms to 4.0 ms to reach steady state.…”

Section: Introduction 1rdre Overviewmentioning

confidence: 99%

“…Figure 2 shows an example of a DMT from three to two waves captured from the RDRE exhaust plane during an experimental run [13]. Additionally, theoretical studies by Koch et al [14], numerical simulations by Lietz et al [8], and wave stability investigations by Anand et al [15], have encountered modal transitions while examining RDE/RDRE nonlinear physics. As such, modal transitions are not isolated incidents.…”

Section: Introductionmentioning

confidence: 99%

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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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Characteristic timescales for detonation-based rocket propulsion systems

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Numerical investigation of operational performance in a methane-oxygen rotating detonation rocket engine

Cited by 23 publications

References 17 publications

Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths

Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths

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

Characteristic timescales for detonation-based rocket propulsion systems

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