Characterization of a multi-injector gox/ch4 combustion chamber
S Silvestri, MP Celano, G Schlieben… - 52nd AIAA/SAE/ASEE …, 2016 - arc.aiaa.org
I. Introduction ydrocarbon propellants are attractive in the space propulsion field due to their
ease in handling and low operational costs. In particular, oxygen/methane is one of the most …
ease in handling and low operational costs. In particular, oxygen/methane is one of the most …
Large Eddy Simulation of Combustion and Heat Transfer in a Single Element GCH4/GOx Rocket Combustor
The single element GCH 4/GOx rocket combustion chamber developed at the Technische
Universität München has been computed using Large Eddy Simulation. The aim of this work …
Universität München has been computed using Large Eddy Simulation. The aim of this work …
Numerical investigation of reacting flow in a methane rocket combustor: turbulence modeling
A Chemnitz, T Sattelmayer, C Roth, O Haidn… - Journal of Propulsion …, 2018 - arc.aiaa.org
A comparison of the numerical predictions of several groups modeling the reacting flow
inside a gaseous methane/gaseous oxygen single-element rocket combustion chamber is …
inside a gaseous methane/gaseous oxygen single-element rocket combustion chamber is …
[PDF][PDF] Large Eddy Simulation of flow and combustion in a single-element GCH4/GOX rocket combustor
A single element GCH4/GOx rocket combustion chamber has been computed, via Large
Eddy Simulation of the experimental combustion rig developed at the Technische Universität …
Eddy Simulation of the experimental combustion rig developed at the Technische Universität …
Simulation of single-injector methane rocket combustor using different numerical codes
A single-injector methane combustion chamber is simulated using two different
computational fluid dynamic codes: TAU and Fluent, density-based and pressure-based …
computational fluid dynamic codes: TAU and Fluent, density-based and pressure-based …
RDE Diluent Mixing & Shock Negation
CA Nordeen, V Ahuja, SB Coogan - AIAA Scitech 2021 Forum, 2021 - arc.aiaa.org
View Video Presentation: https://doi. org/10.2514/6.2021-0902. vid A co-annular diluent
injector and rotating detonation engine exhausts into a convergent conical annulus and …
injector and rotating detonation engine exhausts into a convergent conical annulus and …
Numerical Description of the Turbulent Combustion of Methane-oxygen at 20 atm using the ReduceSens Mechanism
SA Gomez, CR de Andrade, AP Pimenta - AIAA Propulsion and Energy …, 2020 - arc.aiaa.org
ReduceSens is a reaction mechanism developed to describe the chemical kinetics of the
combustion methane-oxygen at high pressures. In this work, ReduceSens and the reduced …
combustion methane-oxygen at high pressures. In this work, ReduceSens and the reduced …
[PDF][PDF] Numerical Analysis on Combustion Instabilities in a Multi-Injector GOX-GCH4 Combustion Chamber
B Zhang, B Wang, XY Hu, O Haidn - epc.ed.tum.de
LOX/LH2 has been widely used in liquid rocket engine for transfer into orbit or space
exploration due to its high specific impulse. The potential of using hydrocarbon as …
exploration due to its high specific impulse. The potential of using hydrocarbon as …
Thermal gas radiation modelling for CFD simulation of rocket thrust chamber
S Johnson, R Lal - 2019 - diva-portal.org
Methane and oxygen are a promising propellant combination in future rocket propulsion
engines mainly due to its advantages like reusability and cost reduction. In order to have a …
engines mainly due to its advantages like reusability and cost reduction. In order to have a …
Thermal gas radiation modelling for CFD simulation of rocket thrust chamber
S Lal, RL Johnson - 2019 - diva-portal.org
Methane and oxygen are a promising propellant combination in future rocket propulsion
engines mainly due to its advantages like reusability and cost reduction. In order to have a …
engines mainly due to its advantages like reusability and cost reduction. In order to have a …