Rotating Detonation Engine Performance Model for Rocket Applications

Stechmann, David P.; Heister, Stephen D.; Harroun, Alexis

doi:10.2514/1.a34313

Cited by 51 publications

(7 citation statements)

References 13 publications

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“…Stechmann et al describe a nozzle design dependent performance model [20,21]. They emphasize the importance of finding an appropriate contour and the fact that mean pressure is not a befitting metric as the RDC benefits greatly from the above-average impulse in each cycle.…”

mentioning

confidence: 99%

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Bach

Stathopoulos

Paschereit

et al. 2020

Combustion and Flame

101

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mentioning

confidence: 99%

Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Bach

Stathopoulos

Paschereit

et al. 2020

Combustion and Flame

101

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“…Of course, other loss mechanisms also exist for the CP engine so the advantage shown still shows promise for the RDRE given the fidelity of the analysis. As with the prior studies [22,23] hydrogen-fueled systems offer the greatest advantages but tend to optimize at very low mixture ratios as indicated in Table 1. From a systems level perspective, this conclusion would need to be revisited given the size of the hydrogen tank implied from these results.…”

Section: Rdre Performancementioning

confidence: 94%

“…A quasi-steady performance treatment was initially developed by Stechmann [21] and subsequently published with colleagues [22]. The model assumes an empirically based pressure waveform to compute quasi-steady conditions for assessing combustion and nozzle performance at various stages in the cycle.…”

Section: Rdre Performancementioning

confidence: 99%

“…The OF ratio was optimized for the CP engine in order to provide a useful comparison of potential performance enhancement. Table 1 also includes average characteristic velocities, C*, as computed from CEA at the conditions noted for the CP engine, and as computed using the waveform-averaged technique from [22,23] for the RDRE. For the conditions noted, potential performance gains range from 3 to 14%.…”

Section: Rdre Performancementioning

confidence: 99%

“…Hydrogen/oxygen detonations show the largest performance benefit of the considered propellants because these detonations have a high degree of shock-heating without as large of a detonation pressure ratio when compared to the other propellants. The lower pressure ratio leads to less stagnation losses when averaging over the entire RDE blowdown cycle [22].…”

Section: Rdre Performancementioning

confidence: 99%

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Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines

et al. 2022

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Rotating (also termed continuous spin) detonation technology is gaining interest in the global research and development community due to the potential for increased performance. Potential performance benefits, thrust chamber design, and thrust chamber cooling loads are analyzed for propellant applications using liquid oxygen or high-concentration hydrogen peroxide oxidizers with kerosene, hydrogen, and methane fuels. Performance results based on a lumped parameter treatment show that theoretical specific impulse gains of 3–14% are achievable with the highest benefit coming from hydrogen-fueled systems. Assessment of thrust chamber designs for notional space missions shows that both thrust chamber length and diameter benefits are achievable given the tiny annular chamber volume associated with the rotating detonation combustion. While the passing detonation front drastically increases local heat fluxes, global energy balances can be achieved if operating pressures are limited to be comparable to existing or prior space engines.

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