Abstract
The accurate numerical simulation of high-pressure rocket combustion chambers is a key element for the design of future space transportation vehicles. In recent years investigations focus more and more on methane-based combustion chambers for which many thermodynamic and combustion issues are still unknown. Experimental investigations indicate that we might have to deal with a close interaction of non-ideal equation-of-state effects together with complex kinetic schemes.
On the numerical side the main challenges include the consistent approximation of thermodynamic effects within a broad temperature range from cryogenic injection up to high temperature effects at combustion. Nowadays simple numerical test cases are missing to study and understand the basic effects during the injection and combustion process, especially with methane as propellant. This open question is addressed by the definition of a simple test case for cryogenic methane combustion and its analysis by applying a range of thermodynamic and kinetic models.
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Acknowledgments
The present work was conducted in the framework of the German Aerospace Center (DLR) project TAUROS (TAU for Rocket Thrust Chamber Simulation) and AMADEUS (Advanced Methods for Reusable Aerospace Vehicle DEsign Using Artificial Intelligence and Interdisciplinary Numerical Simulation) focusing on the qualification and advancement of the DLR flow solver TAU for liquid rocket thrust chamber applications. The financial support of the DLR Space Research Programmatic is highly appreciated.
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Fechter, S., Horchler, T., Karl, S., Hannemann, K. (2021). Generic Numerical Test Case to Understand Cryogenic Methane Combustion Dynamics. In: Pini, M., De Servi, C., Spinelli, A., di Mare, F., Guardone, A. (eds) Proceedings of the 3rd International Seminar on Non-Ideal Compressible Fluid Dynamics for Propulsion and Power. NICFD 2020. ERCOFTAC Series, vol 28. Springer, Cham. https://doi.org/10.1007/978-3-030-69306-0_6
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DOI: https://doi.org/10.1007/978-3-030-69306-0_6
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