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Numerical Simulations of Rocket Combustion Chambers on Massively Parallel Systems

In: High Performance Computing in Science and Engineering ’15

Author

Listed:
  • Roman Keller

    (Institut für Verbrennungstechnik der Luft- und Raumfahrt)

  • Martin Seidl

    (Institut für Verbrennungstechnik der Luft- und Raumfahrt)

  • Markus Lempke

    (Institut für Verbrennungstechnik der Luft- und Raumfahrt)

  • Peter Gerlinger

    (Institut für Verbrennungstechnik der Luft- und Raumfahrt)

  • Manfred Aigner

    (Institut für Verbrennungstechnik der Luft- und Raumfahrt)

Abstract

The compressible, implicit combustion code TASCOM3D is used for the simulation of rocket combustion chambers. Coupled Euler-Lagrange simulations for a subcritical operated model rocket combustor at 5 bar pressure are performed. A quarter of the rectangular combustor is discretized for three-dimensional RANS simulations. Three spray simulations with different initial droplet size distributions are performed. Simulation results exhibit only limited dependency on the initial droplet size distribution. Finally, performance of TASCOM3D on HERMIT and HORNET is compared. A different scaling behavior on both machines with respect to local block size variations is observed.

Suggested Citation

  • Roman Keller & Martin Seidl & Markus Lempke & Peter Gerlinger & Manfred Aigner, 2016. "Numerical Simulations of Rocket Combustion Chambers on Massively Parallel Systems," Springer Books, in: Wolfgang E. Nagel & Dietmar H. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering ’15, edition 1, pages 281-292, Springer.
    • Handle: RePEc:spr:sprchp:978-3-319-24633-8_19
    DOI: 10.1007/978-3-319-24633-8_19
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