Simulation of unsteady combustion in a LOX-GH2 fueled rocket engine |
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| Authors: | M Masquelet S Menon Y Jin R Friedrich |
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| Institution: | 1. School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, USA;2. Technishe Universität München, München, Germany;1. University of Rome “La Sapienza”, Dipartimento di Ingegneria Meccanica e Aerospaziale, Via Eudossiana 18, 00184 Rome, Italy;2. CIRA (Italian Aerospace Research Center), Via Maiorise, 81043 Capua, CE, Italy;1. School of astronautics, Beihang University, Beijng, 100191, China;2. Hypersonic aerodynamics institute of CARDC, Mianyang, 621000, China;1. Scientific Research Institute for System Studies Russian Academy of Sciences, Moscow, Russian Federation;2. Russian Federal Nuclear Center, Russian Scientific Research Institute for Experimental Physics, Sarov, Russian Federation;3. Moscow M.V. Lomonosov State University, Moscow, Russian Federation;1. Russian Federal Nuclear Center – Russian Scientific Research Institute for Experimental Physics, Sarov, Russian Federation;2. Scientific Research Institute for System Studies Russian Academy of Sciences, Moscow, Russian Federation;3. Moscow M.V. Lomonosov State University, Moscow, Russian Federation;1. School of Astronautics, Beihang University, Beijing, 100191, China;2. China Academy of Launch Vehicle Technology, Beijing, 100076, China |
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| Abstract: | This paper presents results from an investigation of unsteady combustion inside a small-scale, multi-injector liquid rocket engine. A time-accurate approach in an axisymmetric geometry is employed to capture the unsteady flow features, as well as the unsteady heat transfer to the walls of the combustion chamber. Both thermally perfect gas (TPG) and real gas (RG) formulations are evaluated for this LOX-GH2 system. The Peng–Robinson cubic equation of state (EoS) is used to account for real gas effects associated with the injection of oxygen. Realistic transport properties are computed but simplified chemistry is used in order to achieve a reasonable turnaround time. Results show the importance of the unsteady dynamics of the flow, especially the interaction between the different injectors. The RG EoS, despite a limited zone of influence, is shown to govern the overall chamber behavior. The sensitivity of the results to changes in the system parameters is studied and some general trends are discussed. Although several features of the simulations agree well with past experimental observations, prediction of heat flux using a simplified flux boundary condition is not completely satisfactory. Reasons for this discrepancy are discussed in the context of the current axisymmetric approach. |
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