Effects of location of an incident shock wave on combustion and flow structure of transverse hydrogen injection

Research output: Contribution to conferencePaperpeer-review

Abstract

Experimental and numerical studies of the interaction between combustion of a hydrogen jet and an incident shock wave were performed. The Mach number of the airstream conditions was 2.5, the total pressure was 0.5 MPa, and the total temperature ranged from 520 K to 870 K. When an incident shock wave was introduced upstream of the injection slot, the boundary-layer separation region was extensively expanded. The penetration height of the Mach disk with an incident shock wave was less than that without an incident shock wave. Combustion was confirmed when the incident shock wave was introduced downstream of the fuel injection slot, but not when it was introduced upstream of the injection slot. The mechanism of these phenomena was analyzed based on the results of numerical simulation in terms of the residence time in the separation region near the fuel injection slot.

Original languageEnglish
Publication statusPublished - 2007
Event6th Asia-Pacific Conference on Combustion, ASPACC 2007 - Nagoya, Japan
Duration: 2007 May 202007 May 23

Conference

Conference6th Asia-Pacific Conference on Combustion, ASPACC 2007
Country/TerritoryJapan
CityNagoya
Period07/5/2007/5/23

ASJC Scopus subject areas

  • Chemical Engineering(all)
  • Energy Engineering and Power Technology
  • Fuel Technology
  • Condensed Matter Physics

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