Development and Testing of a High-Pressure Rotating Detonation Engine for Rocket Applications

Stechmann, David P.; Heister, Stephen D.

doi:10.2514/6.2016-1201

Cited by 3 publications

(8 citation statements)

References 7 publications

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“…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%

“…In addition, the fast-kinetic response of hydrogen fuel has inhibited realization of the predicted performance gains. Using a transverse jet hydrogen injector, Stechmann [21] found that the hydrogen jets themselves tended to serve as flameholders when used in transverse jet injection scheme and as a result only deflagrative performance was realized. Alternate injector concepts may help alleviate this issue but this remains as a challenge to the community.…”

Section: Rdre Performancementioning

confidence: 99%

“…The incorporation of an area contraction within the combustion chamber leads to reflected waves that can interact with the prime detonation front in deleterious manner. Prior work with gOX/gCH4 propellants [21] revealed that incorporation of a throat entirely killed detonation behavior (presumably for this reason), but others have successfully demonstrated throated configurations. For the purposes of the study, this minor design difference would not necessarily affect conclusions.…”

Section: Rdre Thrust Chamber Designmentioning

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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Section: Rdre Performancementioning

confidence: 99%

Section: Rdre Performancementioning

confidence: 99%

Section: Rdre Thrust Chamber Designmentioning

confidence: 99%

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Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines

et al. 2022

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“…An ideal RDE operates as a pressure-gain combustion device where a large portion of the heat release occurs immediately following a high-pressure shock wave that travels circumferentially around a cylindrical or annular chamber [1]. Based on thermodynamic analysis, this cycle could make it possible to increase delivered specific impulse by 10-15% (depending on fuel, oxidizer, chamber pressure, and other parameters) [2][3][4][5]. However, a major factor impacting these estimates is the nozzle efficiency because the device must function over a wide range of pressure ratios.…”

Section: Nomenclaturementioning

confidence: 99%

“…Values in Tables 1 and 2 assume constant of proportionality of unity in Eqs. (1)(2)(3). The relative velocities shown in each case are for a sonic fuel jet at 300 K intersecting a sonic oxidizer sheet at 500 K. These temperatures are representative of typical test conditions in recent Purdue University test campaigns [6].…”

Section: Mixing Considerationsmentioning

confidence: 99%