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

In: High Performance Computing in Science and Engineering '10

Author

Listed:
  • 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)

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.

Suggested Citation

  • Markus Lempke & Peter Gerlinger & Michael Rachner & Manfred Aigner, 2011. "Euler-Lagrange Simulation of a LOX/H2 Model Combustor with Single Shear Coaxial Injector," Springer Books, in: Wolfgang E. Nagel & Dietmar B. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering '10, pages 203-215, Springer.
    • Handle: RePEc:spr:sprchp:978-3-642-15748-6_16
    DOI: 10.1007/978-3-642-15748-6_16
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