Kerosene vs. Methane: A Propellant Tradeoff for Reusable Liquid Booster Stages

Burkhardt, Holger; Sippel, Martin; Herbertz, Armin; Klevanski, Josef

doi:10.2514/1.2672

Cited by 74 publications

(35 citation statements)

References 14 publications

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“…[1][2][3][4][5] Methane is known to be a low-density hydrocarbon having advantages that are similar to those of both kerosene and hydrogen. It is also a cryogenic fuel having a density about six times higher than that of hydrogen, and it requires less insulation and fewer handling concerns than hydrogen.…”

Section: Introductionmentioning

confidence: 99%

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Negishi¹,

Daimon²,

Kawashima³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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In recent years, methane has attracted attention as a propellant for liquid rocket engines because of its various advantages compared to typical propellants such as hydrogen. When methane is used as a coolant for a regenerative cooling system, its near-critical thermodynamic and transport properties experience large variations because its critical pressure is higher than that of typical propellants; this significantly influences the flowfield and heat transfer characteristics. Therefore, adequate understanding of the flowfield and heat transfer characteristics of methane in regenerative cooling channels is a prerequisite for future engine development. In this study, conjugated coolant and heat transfer simulations were performed to investigate the flowfield and heat transfer characteristics of transcritical methane flows in a sub-scale methane-cooled thrust chamber. The computed results were validated against experimental data measured in hot firing tests. They compared well with the measured pressures and temperatures in cooling channels, and wall temperatures were within the permitted levels. Detailed flow analysis revealed peculiar flow structures in the cooling channel: a strong secondary flow induced in the concave-heated part in the channel throat section and the coexistence of two different gas phases-ideal and real-in a single cross-section in the cylindrical region. A high wall temperature appeared in the cylindrical region of the thrust chamber under the considered conditions; this was due to the heat transfer deterioration induced by an M-shaped velocity profile and a turbulentheat flux reduction. Nomenclature a, b,  = coefficients in cubic-type equation of state C p = constant pressure heat capacity G = mass flow rate H = channel height h = heat transfer coefficient Pr = Prandtl number p = pressure q = heat flux R = gas constant Re = Reynolds number R u = universal gas constant s = normal distance T = temperature u = streamwise velocity W = molecular weight x, y, z = coordinate system Z = compressibility factor y + = normalized wall distance 2  = thermal conductivity  = viscosity  = density Subscripts b = bulk c = coolant cr = critical cw = coolant-side wall gw = hot-gas-side wall in = inlet out = outlet t = turbulent throat = throat pcr = pseudo-critical w = wall

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Section: Introductionmentioning

confidence: 99%

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Negishi¹,

Daimon²,

Kawashima³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…The attempts at intentionally causing deactivation only brought the temperature up to 920 K; this temperature was below the point at which coking can occur with methane, 950 K. 11 These backflows occurred at the point where all flows had already ignited so the catalyst temperatures were in excess of 1400 K. The combined effects of the high temperatures, the back flow, and the high pressure resulted in the spoilage of the catalyst. Spoiling was known to occur as immediately after the completion of that firing, the catalyst ceased to function until the proper reactivation cycle was carried out.…”

Section: Deactivationmentioning

confidence: 98%

Development and Testing of a Methane/Oxygen Catalytic Microtube Ignition System for Rocket Propulsion

Deans¹,

Schneider²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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This study sought to develop a catalytic ignition advanced torch system with a unique catalyst microtube design that could serve as a low energy alternative or redundant system for the ignition of methane and oxygen rockets. Development and testing of iterations of hardware was carried out to create a system that could operate at altitude and produce a torch. A unique design was created that initiated ignition via the catalyst and then propagated into external staged ignition. This system was able to meet the goals of operating across a range of atmospheric and altitude conditions with power inputs on the order of 20 to 30 watts with chamber pressures and mass flow rates typical of comparable ignition systems for a 100 lbf engine. • This study developed a catalytic ignition torch system using catalyst microtubes• The goal was to develop a torch igniter similar to traditional spark systems for a 100 lbf engine with reduced power requirement compared to the current state of the art of 70 W needed applied to the exciter of comparable spark hardware• A system was developed using up to 30 W that was able to ignite and create a torch• Breakdown

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“…Moreover, the heat transfer performance of methane is higher compared to other hydrocarbon fuels as a result of its high thermal conductivity, speci¦c heat, and low viscosity. In general, methane shows, compared to other potential candidates, better overall performance from a system point of view [5], higher speci¦c impulse [6], no risks for human health, simple extractability from natural gases, and a density 6 times higher than hydrogen when stored in liquid state at typical tank pressures.…”

Section: Introductionmentioning

confidence: 98%

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Celano

Silvestri

Schlieben

et al. 2016

Progress in Propulsion Physics

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The results from an experimental investigation on an oxygenmethane single-injector combustion chamber are presented. They provide detailed information about the thermal loads at the hot inner walls of the combustion chamber at representative rocket engine conditions and pressures up to 20 bar. The present study aims to contribute to the understanding of the thermal transfer processes and to validate the in-house design tool Thermtest and a base for an attempt to simulate the §ame behavior with large-eddy simulation (LES). Due to the complex §ow phenomena linked to the use of cryogenic propellants, like extreme variation of §ow properties and steep temperature gradients, in combination with intensive chemical reactions, the problem has been partially simpli¦ed by injecting gaseous oxygen (GOx) and gaseous methane (GCH 4 ). external combustion chamber width, m c speci¦c heat capacity, J/(kg·K)' E in total energy entering the control volume, W ' E out total energy leaving the control volume, W

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Kerosene vs. Methane: A Propellant Tradeoff for Reusable Liquid Booster Stages

Cited by 74 publications

References 14 publications

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Flowfield and Heat Transfer Characteristics of Cooling Channel Flows in a Methane-Cooled Thrust Chamber

Development and Testing of a Methane/Oxygen Catalytic Microtube Ignition System for Rocket Propulsion

Injector characterization for a gaseous oxygen-methane single element combustion chamber

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