Euler-Lagrange Simulation of a LOX/H2 Model Combustor with Single Shear Coaxial Injector

Markus Lempke (), Peter Gerlinger, Michael Rachner and Manfred Aigner
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Markus Lempke: Universität Stuttgart, Institut für Verbrennungstechnik der Luft- und Raumfahrt
Peter Gerlinger: Universität Stuttgart, Institut für Verbrennungstechnik der Luft- und Raumfahrt
Michael Rachner: DLR Köln, Institut für Verbrennungstechnik
Manfred Aigner: Universität Stuttgart, Institut für Verbrennungstechnik der Luft- und Raumfahrt

A chapter in High Performance Computing in Science and Engineering '10, 2011, pp 203-215 from Springer

Abstract: Abstract In this paper a mixed Euler-Lagrange approach is used for a 3D simulation of a LOX/H2 model rocket combustor with a single shear coaxial injector. The specific test case presented is the MASCOTTE combustor at 10 bar pressure in the so called A-10 configuration. The simulation of the gas phase is conducted with the scientific code TASCOM3D which works in an Eulerian mode while the liquid fuel droplets are treated by the scientific code SPRAYSIM in a Lagrangian framework. The two codes and the coupling mechanisms are explained and results of a preliminary simulation will be presented. At the end an outlook is given focusing on how to obtain an even more accurate representation of the experiment in subsequent simulations. Finally some comments on the computational costs of the calculations and the performance of the two codes on the NEC SX-9 are given.

Keywords: Combustion Chamber; High Performance Computing; Liquid Oxygen; Species Mass Fraction; Model Combustor (search for similar items in EconPapers)
Date: 2011
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-642-15748-6_16

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DOI: 10.1007/978-3-642-15748-6_16

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