Effects of incident shock wave on combustion downstream of ramp injector in supersonic flow

Yoshitaka Iwamura, Taku Kudo, Hideaki Kobayashi

Research output: Contribution to conferencePaperpeer-review

1 Citation (Scopus)

Abstract

Experiments and numerical simulations were conducted to explore the interaction between an incident shock wave and a flame holding region downstream of a ramp injector. The Mach number of the airstream was 2.5, the total pressure was 0.5 MPa, and the total temperature ranged from 520 K to 730 K. Once a ramp injector is set in Supersonic flow, it generates an oblique shock wave from its leading edge. Thus, a pressure gradient is formed between ramp and sidewall, which induces vertical vortices downstream of the ramp injector. High mixing performance is expected due to the vertical vortices. In this study, when an incident shock wave was introduced, a flame-holding region was formed downstream of the incident shock wave, while without it, no apparent flame-holding region was observed. The mechanisms of these phenomena were analyzed based on the results of numerical simulation.

Original languageEnglish
Publication statusPublished - 2013 Jan 1
Event9th Asia-Pacific Conference on Combustion, ASPACC 2013 - Gyeongju, Korea, Republic of
Duration: 2013 May 192013 May 22

Other

Other9th Asia-Pacific Conference on Combustion, ASPACC 2013
CountryKorea, Republic of
CityGyeongju
Period13/5/1913/5/22

ASJC Scopus subject areas

  • Environmental Engineering

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