3D Simulations of Supersonic Chemically Reacting Flows

Fernando Schneider, Peter Gerlinger and Manfred Aigner
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Fernando Schneider: DLR Stuttgart, Institut für Verbrennungstechnik
Peter Gerlinger: DLR Stuttgart, Institut für Verbrennungstechnik
Manfred Aigner: DLR Stuttgart, Institut für Verbrennungstechnik

A chapter in High Performance Computing in Science and Engineering ’03, 2003, pp 267-276 from Springer

Abstract: Summary The mixing and combustion of hydrogen in a model scramjet (supersonic combustion ramjet) engine is investigated numerically. For an improved mixing a lobed strut injector is employed. It will be shown that due to the chosen shape of the injector strong streamwise vortices are induced which improve the mixing and therefore shorten the necessary combust or length. The hydrogen is injected with Mach 1.4 into a Mach 2 supersonic air flow. Computational grids with 0.43 and 3.2 million volumes have been used for these combustion simulations. Due to the complex physical phenomena in high speed flows extremely fine grids are required in the vicinity of walls. The use of finite-rate chemistry additionally causes long computational times. The chosen chemistry reaction mechanism employs 20 reactions and 9 different species. Thus efficient numerical solvers are required as well as facilities that allow high performance computing. The numerical code is parallelized by domain decomposition using MPI and the simulations shown are performed on a Cray T3E using up to 208 nodes.

Keywords: Streamwise Vortex; Supersonic Combustion; Combustion Investigation; Combustion Simulation; Scramjet Combustor (search for similar items in EconPapers)
Date: 2003
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-642-55876-4_20

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DOI: 10.1007/978-3-642-55876-4_20

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