Numerical Investigation of Flow and Combustion in a Single Element GCH4/Gox Rocket Combustor

Roth, C.; Haidn, Oskar; Chemnitz, A.; Sattelmayer, Thomas; Frank, Gabriele; Müller, Hagen; Zips, Julian; Keller, R.; Gerlinger, Peter; Maestro, Dario; Cuenot, Bénédicte; Riedmann, Hendrik; Selle, Laurent

doi:10.2514/6.2016-4995

Cited by 20 publications

(22 citation statements)

References 10 publications

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“…For a detailed description of the calculation strategies used by the different groups the reader is referred to Roth et al 1 Here only a brief description is provided, focusing on the relevant aspects with respect to the proposed analysis. A summary is given in table 3.…”

Section: B Numerical Approachmentioning

confidence: 99%

“…The different approaches are here compared and analyzed to understand how chemistry and TCI contribute to the differences between the numerical solutions and to the experiment. A comparison to experimental data can be found in Roth et al 1 The role of turbulence is studied in more detail in Chemnitz et al 2 First, the two chemical schemes are described and evaluated against a detailed one for canonical flame configurations. Then the different simulations are presented and compared in terms of global flame shape and flow structure.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of Flow and Combustion in a Single-Element GCH₄/GOX Rocket Combustor: Chemistry Modeling and Turbulence-Combustion Interaction

Maestro¹,

Cuenot²,

Chemnitz³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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A sub-scale GOx/GCH4 rocket combustor has been simulated by different groups using various numerical methods. The current contribution focuses on the effects of chemistry and combustion modeling on the turbulent flame shape and structure, as well as the resulting axial pressure profile and wall heat flux, for which experimental data are available. Two different kinetic schemes have been used, combined with various models for turbulence and turbulence-combustion interaction (TCI). To evaluate the impact of combustion chemistry, the schemes are first studied on canonical laminar flames and evaluated against a detailed chemical scheme. The results obtained by the different groups on the target configuration demonstrate the strong impact of the models and the consequences for pressure and wall heat flux prediction.

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Section: B Numerical Approachmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Flow and Combustion in a Single-Element GCH₄/GOX Rocket Combustor: Chemistry Modeling and Turbulence-Combustion Interaction

Maestro¹,

Cuenot²,

Chemnitz³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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“…C. Roth et al also discussed simulation results based on a single injector methane-oxygen case, where unless generally nice results the heat release was not computed sufficiently well, which was likely due to improper mixing modeling. 10 Chemnitz et al 11 studying the same single-injector case found that the differences in mixing behavior originate from the fields of turbulent viscosity, which means the key effect of the turbulence model behavior.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of reacting flow in the combustion chamber and study of the impact of turbulent diffusion coefficients

Strokach

Borovik

Chen

2014

Advances in Mechanical Engineering

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A methodology for combustion modeling with complex mixing and thermodynamic conditions, especially in thrusters, is still under development. The resulting flow and propulsion parameters strongly depend on the models used, especially on the turbulence model as it determines the mixing efficiency. In this paper, the effect of the sigma-type turbulent diffusion coefficients arriving in the diffusion term of the turbulence model is studied. This study was performed using complex modeling, considering the conjugate effect of several physical phenomena such as turbulence, chemical reactions, and radiation heat transfer. To consider the varying turbulent Prandtl, an algebraic model was implemented. An adiabatic steady diffusion Flamelet approach was used to model chemical reactions. The P1 differential model with a WSGG spectral model was used for radiation heat transfer. The gaseous oxygen (GOX) and methane (GCH4) operating thruster developed at the Chair of turbomachinery and Flight propulsion of the Technical University of Munich (TUM) is taken as a test case. The studies use the 3D RANS approach using the 60° sector as the modeling domain. The normalized and absolute pressures, the integral and segment averaged heat flux are compared to numerical results. The wall heat fluxes and pressure distributions show good agreement with the experimental data, while the turbulent diffusion coefficients mostly influence the heat flux.

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“…However, results of a new test including the measure of coolant temperature increase in throat region have been made recently available [5,6]. These data have been considered a testbench for code validation by different Dipartimento di Ingegneria Meccanica ed Aerospaziale, "La Sapienza"-Università di Roma, Rome, Italy research groups making use of both commercial and inhouse CFD software [7][8][9][10][11][12][13][14][15]. In this paper, some aspects of modeling are deepened to get more insight on the driving phenomena for the correct prediction of throat heat flux.…”

Section: Introductionmentioning

confidence: 99%

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

Concio

Migliorino

Nasuti

2020

Aerotec. Missili Spaz.

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The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challenge, because of the little experimental information. Such a problem is of obvious importance in general, and becomes even more important when considering reusable engines. Unfortunately, only few indirect experimental data are available for the validation of throat heat flux prediction. On the numerical side, a detailed solution would require a huge resolution and codes able to solve at the same time combustion, boundary layer with possible finite-rate reactions, expansion up to at least sonic speed, and in some cases radiative heat flux. Therefore, it is important to validate, with the few experimental data available in the literature, simplified CFD approaches whose aim is to predict heat flux in the nozzle in affordable times. Results obtained by different numerical models based on a RANS approach show the correctness and quality of the approximations made, indicating the main phenomena to be included in modeling for the correct prediction of throat heat flux.

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Numerical Investigation of Flow and Combustion in a Single Element GCH4/Gox Rocket Combustor

Cited by 20 publications

References 10 publications

Numerical Investigation of Flow and Combustion in a Single-Element GCH₄/GOX Rocket Combustor: Chemistry Modeling and Turbulence-Combustion Interaction

Numerical Investigation of Flow and Combustion in a Single-Element GCH₄/GOX Rocket Combustor: Chemistry Modeling and Turbulence-Combustion Interaction

Numerical simulation of reacting flow in the combustion chamber and study of the impact of turbulent diffusion coefficients

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

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Numerical Investigation of Flow and Combustion in a Single Element GCH4/Gox Rocket Combustor

Cited by 20 publications

References 10 publications