A liquid propulsion panorama

Caisso, Philippe; Souchier, A.; Rothmund, Christophe; Alliot, Patrick; Bonhomme, C.; Zinner, W.; Parsley, R. C.; Neill, Todd; Forde, Scott; Starke, R. G.; Wang, William Yang; Takahashi, Mamoru; Atsumi, Masahiro; Valentian, Dominique

doi:10.1016/j.actaastro.2009.04.020

Cited by 39 publications

(16 citation statements)

References 30 publications

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“…It is worth noting that a detailed consideration of the acceleration term reveals that diffusion-like contributions will also arise in the Right Hand Side (RHS) of Eq. (1). Finally, the term Q(F, F) that appears in Eq.…”

Section: ∂F ∂Tmentioning

confidence: 96%

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Lagrangian modelling of turbulent spray combustion under liquid rocket engine conditions

2014

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Section: ∂F ∂Tmentioning

confidence: 96%

“…Moreover, hydrogen is a reference fuel for scramjet and rocket applications [1] as it delivers the highest possible heat release within the shortest possible kinetic time. The wide range of flammability of hydrogen combined with its high diffusivity promote the ignition of reactive mixtures in extreme conditions.…”

Section: Introductionmentioning

confidence: 99%

Lagrangian modelling of turbulent spray combustion under liquid rocket engine conditions

2014

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“…Navarro et al [13] had developed a multipurpose optically accessible rocket chamber designed for producing 11.3 kg of thrust at 20 bar operating pressure using LOX and CH 4 as propellants. Caisso et al [14] provided a brief review of the historical development, current observed trends, and possible areas of improvements in liquid propulsion systems with a roadmap of future developments.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of combustion in a hydrocarbon and gaseous oxygen fuelled rocket

Shaikh

Patidar

Chowdhury

2017

Applied Thermal Engineering

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“…1,2 Methane as a fuel can provide a higher specific impulse, together with better cooling capabilities and less soot deposition than other hydrocarbons. Moreover, differently than oxygen/hydrogen propellant combination, oxygen/methane can be considered space storable and is favored by higher density.…”

Section: Introductionmentioning

confidence: 99%

Cooling Channel Analysis of a LOX/LCH4 Rocket Engine Demonstrator

Pizzarelli¹,

Betti

Nasuti

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A computational procedure able to describe the coupled hot-gas/wall/coolant environment that occurs in most liquid rocket engines is presented and demonstrated. The coupled analysis is performed by loose coupling of the two-dimensional axisymmetric Reynolds-Averaged Navier-Stokes equations for the hot-gas flow and the conjugate three-dimensional model for the coolant flow and solid material heat transfer in the regenerative cooling circuit. The latter model is in turn based on the coupled Reynolds-Averaged Navier-Stokes equations for the coolant flow and Fourier equation for the thermal conduction in the solid material. In this study, the thermal behavior of a regeneratively cooled oxygen/methane engine demonstrator is analyzed in detail. Starting from a nominal operative condition of the engine, different levels of channel surface roughness and coolant mass flow rate are considered in order to understand their influence on the heat transfer capability of the cooling system. Results show that the heat transfer can be markedly impaired if the operating parameters undergo rather minor changes with respect to the nominal condition

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A liquid propulsion panorama

Cited by 39 publications

References 30 publications

Lagrangian modelling of turbulent spray combustion under liquid rocket engine conditions

Lagrangian modelling of turbulent spray combustion under liquid rocket engine conditions

Experimental and numerical investigation of combustion in a hydrocarbon and gaseous oxygen fuelled rocket

Cooling Channel Analysis of a LOX/LCH4 Rocket Engine Demonstrator

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