Inverse heat transfer method applied to capacitively cooled rocket thrust chambers

Large-eddy simulations are carried out for the coaxial injection of liquid nitrogen and preheated hydrogen at supercritical pressures. The conditions are similar to that in typical liquid-propellant rocket combustors. By using nitrogen as a model gas, the mixing process is studied without the interference with chemical reactions. An analysis of the thermodynamic conditions that arise in the shear layer reveals that local phase separation may occur if the injection condition is transcritical. A novel volume-translation method on the basis of the cubic Peng–Robinson equation of state is introduced for the use in multispecies large-eddy simulations and is tested for both trans- and supercritical injection conditions. The new thermodynamic model corrects the deficiencies of the Peng–Robinson equation of state in the transcritical regime at minimal extra computational cost. Two independently developed large-eddy simulation codes are used for the simulations and the results are compared. The outcome indicates t...

Large-Eddy Simulation of Coaxial LN2/GH2 Injection at Trans- and Supercritical Conditions

Data-assisted combustion simulations with dynamic submodel assignment using random forests

In the present Paper, the simulation of the flow inside an experimental GOX/GCH4 rocket thrust chamber is undertaken. The combustor’s injector consists of seven individual coaxial injector elements...

Heat Transfer and Combustion Simulation of Seven-Element O2/CH4 Rocket Combustor

Time-resolved flow field and thermal loads in a single-element GOx/GCH4 rocket combustor

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 conducted. The focus is pl...

Numerical Investigation of Reacting Flow in a Methane Rocket Combustor: Turbulence Modeling

The flow and combustion in a GCH4/GOX single-element rocket combustor is analysed by several groups using different numerical models and tools. The tools and simulation setups vary with respect to modeling fidelity and computational expense. A short overview of the tools and the individual simulation setups is given. The focus of the paper is the comparison of the results obtained by the different groups as well as with experimental data. This encompasses the study of specific features of the combustor flow among the different simulations, as well as the validation with typical rocket engine design and performance parameters, such as wall heat flux and combsution pressure, gained from hot firing tests.

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

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Numerical Modeling of Flow and Combustion in a Single-Element GCH4/GOx Rocket Combustor: Aspects of Turbulence Modeling

A comparison of the numerical predictions of several groups modeling the reacting flow inside a GCH4/GOX single element rocket combustion chamber is conducted. The focus is placed on turbulence quantities and their influence on the computed mean fields. However, subject of this paper is not a pure study of turbulence model variation but it aims at showing their effect within the framework of different overall setups. These comprise differences in combustion models as well as codes used. Several RANS approaches incorporating the Boussinesq approximation for the modeling of Reynolds stresses are considered. Turbulent heat and mass transfer are modeled via turbulent Prandtl and Schmidt numbers. Characteristic tendencies of the turbulence models are observed across the different codes and combustion models. Furthermore, the relevance of turbulence modeling parameters depends on the combustion modeling approach. An influence of the code used is found as well.

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

The present paper focuses on the numerical modeling of the combustion and heat transfer processes occurring in a GCH4/GOX rocket combustor, which was tested experimentally at the Technical University of Munich. A CFD model, using a RANS formulation to resolve the turbulent flow in the combustor, is set up and a grid independence study is performed. Three different combustion models are applied and the results are compared among each other, as well as to the experimental data. The applied models are an equilibrium chemistry model, a non-adiabatic flamelet model, and laminar finite rate chemistry. The models vary in fidelity as well as computational expense. Their ability to resolve the underlying physical processes of the reactive flow in the combustion chamber is investigated and discussed.

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Christof M. Roth

Papers

Numerical Investigation of Reacting Flow in a Methane Rocket Combustor: Turbulence Modeling

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

Numerical Modeling of Flow and Combustion in a Single-Element GCH4/GOx Rocket Combustor: Aspects of Turbulence Modeling

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

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