Experimental and Numerical Investigation of a Multi-Injector GOX-GCH4 Combustion Chamber

Silvestri, Simona; Kirchberger, Christoph; Schlieben, Gregor; Celano, M.P.; Haidn, Oskar

doi:10.2322/tastj.16.374

Cited by 12 publications

(11 citation statements)

References 11 publications

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“…This combustion chamber was experimentally investigated at the Technical University of Munich [22]. Seven coaxial injectors supply gaseous oxygen and gaseous methane at an oxidizer-to-fuel ratio (O/F) of 2.65.…”

Section: Multi-injector Combustion Chambermentioning

confidence: 99%

“…The inner diameter of the chamber is 30 mm, its nozzle diameter 19 mm and the length 341 mm. More details concerning the experimental setup can be found in [22].…”

Section: Multi-injector Combustion Chambermentioning

confidence: 99%

“…Symmetry boundary conditions are applied at both symmetry planes. The wall of the combustion chamber is assumed to be isothermal with wall temperature values stemming from the experiment [22]. At the inlet, a mass flow rate is prescribed and the outlet uses a supersonic outflow condition.…”

Section: Multi-injector Combustion Chambermentioning

confidence: 99%

“…Comparison of wall pressure (left) and wall heat flux (right) with the experiment[22] Temperature profiles at the symmetry plane y = 0 m (top) and two different axial locations (bottom). Note that the plane at the top is compressed by a factor of 4 in axial direction…”

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confidence: 99%

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Rocket Combustion Chamber Simulations Using High-Order Methods

Seitz

Lechtenberg

Gerlinger

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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High-order spatial discretizations significantly improve the accuracy of flow simulations. In this work, a multi-dimensional limiting process with low diffusion (MLP$$^\text {ld}$$) and up to fifth order accuracy is employed. The advantage of MLP is that all surrounding volumes of a specific volume may be used to obtain cell interface values. This prevents oscillations at oblique discontinuities and improves convergence. This numerical scheme is utilized to investigate three different rocket combustors, namely a seven injector methane/oxygen combustion chamber, the widely simulated PennState preburner combustor and a single injector chamber called BKC, where pressure oscillations are important.

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Section: Multi-injector Combustion Chambermentioning

confidence: 99%

“…The inner diameter of the chamber is 30 mm, its nozzle diameter 19 mm and the length 341 mm. More details concerning the experimental setup can be found in [22].…”

Section: Multi-injector Combustion Chambermentioning

confidence: 99%

Section: Multi-injector Combustion Chambermentioning

confidence: 99%

mentioning

confidence: 99%

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Rocket Combustion Chamber Simulations Using High-Order Methods

Seitz

Lechtenberg

Gerlinger

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…A paper by Silvestri et al gives detailed data concerning the test bench and experimental setting. 6–8…”

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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