Heat flux evaluation in a multi-element CH4/O2 rocket combustor using an inverse heat transfer method

Perakis, Nikolaos; Strauß, Julian; Haidn, Oskar

doi:10.1016/j.ijheatmasstransfer.2019.07.075

Cited by 21 publications

(27 citation statements)

References 34 publications

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“…The temperature dependent properties are obtained using the NIST database [17]. More details about the method can be found in [21].…”

Section: Modeling the Cooling Channelsmentioning

confidence: 99%

“…For each axial position, the heat flux resulting from the inverse method is plotted with the markers representing the values at the parameter points and the solid lines representing the azimuthal heat flux profile applied at the wall. The uncertainty intervals calculated as described in [21] are shown as shadows and amount to ±10%−30% of the average values. It is easy to notice by looking at Fig.…”

Section: Experimental Azimuthal Heat Flux Profilesmentioning

confidence: 99%

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Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Perakis

Haidn

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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The experimental investigation of sub-scale rocket engines gives significant information about the combustion dynamics and wall heat transfer phenomena occurring in full-scale hardware. At the same time, the performed experiments serve as validation test cases for numerical CFD models and for that reason it is vital to obtain accurate experimental data. In the present work, an inverse method is developed able to accurately predict the axial and circumferential heat flux distribution in CH$$_4$$/O$$_2$$ rocket combustors. The obtained profiles are used to deduce information about the injector-injector and injector-flame interactions. Using a 3D CFD simulation of the combustion and heat transfer within a multi-element thrust chamber, the physical phenomena behind the measured heat flux profiles can be inferred. A very good qualitative and quantitative agreement between the experimental measurements and the numerical simulations is achieved.

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“…The temperature dependent properties are obtained using the NIST database [17]. More details about the method can be found in [21].…”

Section: Modeling the Cooling Channelsmentioning

confidence: 99%

Section: Experimental Azimuthal Heat Flux Profilesmentioning

confidence: 99%

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Perakis

Haidn

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…The other wall faces were modeled with a no-slip adiabatic setting. Due to the previously discussed ambiguities in the nozzle heat flux estimations, 12,13 no comparison between the experimental and CFD data for the nozzle was produced, as the current research was focused on the fields and integral parameters in the cylindrical part of the combustor. The nozzle temperature was set equal to the last value of the temperature profile in the cylindrical part.…”

Section: Numerical Setupmentioning

confidence: 99%

“…Most of the research papers on the present and other typical combustors applied a resolving-to-the-wall grid to satisfy the y + ≈ 1 condition. 6,12,13,29 Some groups focus on the development of wall-functions, but now it is mainly coupled with LES based turbulence modeling. 10,11,29–35 In this study, a default near-modeling approach being coupled with RANS was used, namely an “Automatic wall treatment”, which CFX implements 28 and proposes a smooth shift from a resolved viscous sublayer to a coarser wall-function based method for logarithmic region, which can make the engineering optimization routine computations in industry more fast and easy.…”

Section: Numerical Setupmentioning

confidence: 99%

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

Strokach

Borovik

Chen

2020

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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