Application of non-toxic propellants for future launch vehicles

Goetz, Andreas; Maeding, C.; Brummel, L.; Haeseler, D.

doi:10.2514/6.2001-3546

Cited by 10 publications

(3 citation statements)

References 4 publications

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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: 99%

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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Section: Introductionmentioning

confidence: 99%

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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“…2 In addition less soot deposition is observed for methane oxidation compared to kerosene. 3 Methane is easier to store in comparison to hydrogen because of its higher molecular weight and is therefore a better choice for in-space application with long durations. The higher density of methane compared to hydrogen allows for smaller fuel tanks (less structure mass) and yields less pumped volume over time for the turbo pumps.…”

Section: Introductionmentioning

confidence: 99%

A Numerical Model for Nozzle Flow Application under LOX/CH4 Hot Flow Conditions

Schneider¹,

Génin²,

Karl³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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“…These candidates present several advantages like higher density, reduced handling e¨ort (reduced safety precautions), and easier storage (lower cooling e¨ort). Moreover, several precedent studies have highlighted speci¦c advantages of methane [1], namely, better cooling capabilities, a higher speci¦c impulse, and lower coking and sooting propensities (at both, the cooling channel and combustion chamber walls).…”

Section: Urjuhvv Lq 3ursxovlrq 3k\vlfv '2 Hxfdvv 2zqhg E\ Wkh Dxwkrmentioning

confidence: 99%

Ignition of a gaseous methane/oxygen coaxial jet

Pauly¹,

Sender²,

Oschwald³

2009

Progress in Propulsion Physics

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Ignition and §ame anchoring of a coaxial gaseous methane oxygen jet have been studied using high-speed visualization techniques. Several ignition scenarios (¤blowout,¥ ¤smooth,¥ and ¤strong ignition¥) have been found with speci¦c phenomenology depending, mainly, on the time delay between propellant valve opening and ignition. The time necessary for §ame anchoring is shown to depend on the mass §ow rate. Attached and detached §ames are observed and it is found that high momentum §ux ratios favour the establishment of a §ame attached to the injector. For detached §ames, higher chamber pressures result in smaller liftod istances. NOMENCLATURE CC combustion chamber d, Dinner diameter, outer diameter fps frames per second GO 2 gaseous oxygen GCH 4 gaseous methane J momentum §ux ratio,velocity ratio, V ratio = u CH4 /u O2 ρ density equivalence ratio

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Application of non-toxic propellants for future launch vehicles

Cited by 10 publications

References 4 publications

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

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

A Numerical Model for Nozzle Flow Application under LOX/CH4 Hot Flow Conditions

Ignition of a gaseous methane/oxygen coaxial jet

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