Liquid Fuel Survey for Rotating Detonation Rocket Engines

Harroun, Alexis; Heister, Stephen D.

doi:10.2514/6.2022-0088

Cited by 4 publications

(1 citation statement)

References 11 publications

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“…The extent to which vaporization plays a role in cyrogenic fluids such as liquid oxygen (LOX) or high vapor pressure propellants such as nitrogen tetroxide (NTO) has not been established to any significant degree. Our group has made some initial efforts using the Cheetah tool with various assumptions regarding mixedness with exhaust products [17,18]. In general, these models generate more questions than answers, primarily due to the computation of real gas conditions at the gigantic pressure levels predicted by the Cheetah code.…”

Section: Rdre Performancementioning

confidence: 99%

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%