Auto ignition in a supersonic combustor with perpendicular injection behind backward-facing step

Sadatake Tomioka, Tetsuo Hiraiwa, Toliru Mitani, Yoshihiko Zamma, Hiroyuki Shiba, Goro Masuya

Research output: Contribution to conferencePaper

3 Citations (Scopus)

Abstract

Flow field at pre-ignition phase in a supersonic combustor with perpendicular injections behind a backward facing step was simulated in cold flow tests with inert gas injection, to investigate the mechanism of the ignition enhancement observed in the ignition tests with the same combustor. The interaction, namely the merging, of separation at step base with that upstream of the injector caused enlargement of ignition region and the enhancement. The change in ignition ability was estimated based on ignition parameters. Based on the experimentally obtained ignition parameters, the ignition limit for the interacted separation region was predicted and showed reasonable agreement with the experimental results.

Original languageEnglish
Publication statusPublished - 1997 Jan 1
Event33rd Joint Propulsion Conference and Exhibit, 1997 - Seattle, United States
Duration: 1997 Jul 61997 Jul 9

Other

Other33rd Joint Propulsion Conference and Exhibit, 1997
CountryUnited States
CitySeattle
Period97/7/697/7/9

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

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  • Cite this

    Tomioka, S., Hiraiwa, T., Mitani, T., Zamma, Y., Shiba, H., & Masuya, G. (1997). Auto ignition in a supersonic combustor with perpendicular injection behind backward-facing step. Paper presented at 33rd Joint Propulsion Conference and Exhibit, 1997, Seattle, United States.