Numerical Simulations of Rocket Combustion Chambers on Massively Parallel Systems

Roman Keller (), Martin Seidl, Markus Lempke, Peter Gerlinger and Manfred Aigner
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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

A chapter in High Performance Computing in Science and Engineering ’15, 2016, pp 281-292 from Springer

Abstract: 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.

Keywords: Combustion Chamber; Rocket Engine; RANS Simulation; Species Mass Fraction; Delayed Detach Eddy Simulation (search for similar items in EconPapers)
Date: 2016
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-319-24633-8_19

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DOI: 10.1007/978-3-319-24633-8_19

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