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Effects of streamwise vortex breakdown on supersonic combustion

Toshihiko Hiejima*

  • Department of Aerospace Engineering, Osaka Prefecture University, 1-1 Gakuen-cho, Nakaku, Sakai, Osaka 599-8531, Japan

  • *hiejima@aero.osakafu-u.ac.jp
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Phys. Rev. E 93, 043115 – Published 14 April, 2016

DOI: https://doi.org/10.1103/PhysRevE.93.043115

Abstract

This paper presents a numerical simulation study of the combustion structure of streamwise vortex breakdown at Mach number 2.48. Hydrogen fuel is injected into a combustor at sonic speed from the rear of a hypermixer strut that can generate streamwise vortices. The results show that the burning behavior is enhanced at the points of the shock waves that are incident on the vortex and therefore the vortex breakdown in the subsonic region occurs due to combustion. The breakdown domain in the mainstream is found to form a flame-holding region suited to combustion and to lead to a stable combustion field with detached flames. In this way, streamwise vortex breakdown has an essential role in combustion enhancement and the formation of flames that hold under supersonic inflow conditions. Finally, the combustion property defined here is shown to coincide with the produced-water mass flow. This property shows that the amount of combustion is saturated at equivalence ratios over 0.4, although there is a slight increase beyond 1.

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Outline

Information

Phys. Rev. E 93, 043115– Published 14 April, 2016
  • Received 19 November 2015
  • Revised 2 February 2016

©2016 American Physical Society

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