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Enhanced Mixing in Supersonic Combustion

In: High Performance Computing in Science and Engineering’ 04

Author

Listed:
  • Fernando Schneider

    (DLR Stuttgart, Institut für Verbrennungstechnik)

  • Peter Gerlinger

    (DLR Stuttgart, Institut für Verbrennungstechnik)

  • Manfred Aigner

    (DLR Stuttgart, Institut für Verbrennungstechnik)

Abstract

To control the reaction progress in supersonic combustors the fuel/air mixing has to be optimized which is investigated numerically in this paper. The mixing process is strongly influenced by the design of the fuel strut injector. Optimization studies may help to improve the mixing efficiency of real size scramjet (supersonic combustion ramjet) engines. The strut design used in this paper is the result of previous experimental and numerical investigations [1, 2, 3]. It has been verified that the use of lobed strut injectors improves the mixing by generation of streamwise vortices in the core region of the combustion chamber. The present study compares two different nozzle exit designs using basically the same strut shape. 295 K cold hydrogen is injected with Mach 2.0 into a 1300 K hot Mach 2.0 supersonic air flow.

Suggested Citation

  • Fernando Schneider & Peter Gerlinger & Manfred Aigner, 2005. "Enhanced Mixing in Supersonic Combustion," Springer Books, in: Egon Krause & Willi Jäger & Michael Resch (ed.), High Performance Computing in Science and Engineering’ 04, pages 213-223, Springer.
    • Handle: RePEc:spr:sprchp:978-3-540-26589-4_22
    DOI: 10.1007/3-540-26589-9_22
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