Modeling Combustion and Heat Transfer in a Single-Element GCH4/GOX Rocket Combustor

Roth, C.; Perakis, Nikolaos; Haidn, Oskar

doi:10.11159/ffhmt20.178

Cited by 2 publications

(2 citation statements)

References 7 publications

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“…The mentioned process of reducing the propellant's inlet enthaply in CEA to account for heat losses was e.g. also used by Roth, Perakis and Haidn [41]. Due to the large * (3.10 m, = 0.1405 m) in this previous test series the combustion efficiency was only in between 74% and 92%.…”

Section: A Results Of Previous Tests: Influence Of Mixture Ratio On *mentioning

confidence: 91%

Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

Werling

Bätz

2022

Journal of Propulsion and Power

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Currently several green propellants are under investigation to replace the toxic and carcinogenic monopropellant hydrazine (N 2 H 4 ). Beside alternatives as Ammonium dinitramide (ADN)-based propellants, Hydroxylammonium nitrate (HAN)-based mixtures or high concentrated hydrogen peroxide (H 2 O 2 ), mixtures of fuels with nitrous oxide -called HyNOx or NOFBX represent promising green propellants. Compared to classical hydrazine, N 2 O/fuel mixtures offer a higher performance ( , * ), no or low toxicity and low propellant costs. To investigate the handling and performance of a propellant mixture consisting of nitrous oxide (N 2 O) and ethene (C 2 H 4 ), hot gas combustion tests with an experimental combustor were conducted. This paper summarizes the results of 134 combustion tests conducted with the premixed propellant injected in gaseous state. Calculated and measured performance ( * and * ) depending on mixture ratio, characteristic combustion chamber length ( * ) and chamber pres-* ℎ

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Section: A Results Of Previous Tests: Influence Of Mixture Ratio On *mentioning

confidence: 91%

Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

Werling

Bätz

2022

Journal of Propulsion and Power

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“…Roth et al [6] performed a comparative study of the combustion models, using the same single-injector coaxial combustor from TUM. The study, aiming to comparing a finiterate model, a non-adiabatic flamelet model, and an equilibrium chemistry model in a FANS, found that the finite-rate approach resulted in the best performance.…”

Section: Introductionmentioning

confidence: 99%

Simulation of a GOx-GCH4 Rocket Combustor and the Effect of the GEKO Turbulence Model Coefficients

et al. 2021

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In this study, a single injector methane-oxygen rocket combustor is numerically studied. The simulations included in this study are based on the hardware and experimental data from the Technical University of Munich. The focus is on the recently developed generalized k–ω turbulence model (GEKO) and the effect of its adjustable coefficients on the pressure and on wall heat flux profiles, which are compared with the experimental data. It was found that the coefficients of ‘jet’, ‘near-wall’, and ‘mixing’ have a major impact, whereas the opposite can be deduced about the ‘separation’ parameter Csep, which highly influences the pressure and wall heat flux distributions due to the changes in the eddy-viscosity field. The simulation results are compared with the standard k–ε model, displaying a qualitatively and quantitatively similar behavior to the GEKO model at a Csep equal to unity. The default GEKO model shows a stable performance for three oxidizer-to-fuel ratios, enhancing the reliability of its use. The simulations are conducted using two chemical kinetic mechanisms: Zhukov and Kong and the more detailed RAMEC. The influence of the combustion model is of the same order as the influence of the turbulence model. In general, the numerical results present a good or satisfactory agreement with the experiment, and both GEKO at Csep = 1 or the standard k–ε model can be recommended for usage in the CFD simulations of rocket combustion chambers, as well as the Zhukov–Kong mechanism in conjunction with the flamelet approach.

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Modeling Combustion and Heat Transfer in a Single-Element GCH4/GOX Rocket Combustor

Cited by 2 publications

References 7 publications

Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

Parameters Influencing the Characteristic Exhaust Velocity of a Nitrous Oxide/Ethene Green Propellant

Simulation of a GOx-GCH4 Rocket Combustor and the Effect of the GEKO Turbulence Model Coefficients

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