超音速燃焼器内の自発着火領域に関する数値解析  [in Japanese] Numerical Investigation of Autoignition Region in a Supersonic Combustor  [in Japanese]

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Abstract

The present paper deals with the numerical investigation of autoignition region between a backward-facing step and perpendicular wall injectors in a supersonic combustor. A series of simulation changing the dynamic pressure ratio of the injectant to the main stream is carried out. Wall pressure profiles and injectant concentration in the recirculation region between the step and the injectors show agreement with experimental results. The results by tracking streamline clarifies the correlation between the ratio of circulating cycle to the variation of injectant concentration in the horseshoe vortex and the residence time of mixture measured at the fixed point. The residence time increases from 0.3 msec at the dynamic pressure ratio of 0.1 to 1.2 msec at 0.7. When the dynamic pressure ratio exceeds 0.7, the residence time becomes constant because the size of the horseshoe vortex and injectant concentration does not vary.

Journal

  • JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 50(580), 181-187, 2002-05-05

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

References:  11

Cited by:  1

Codes

  • NII Article ID (NAID)
    10008213674
  • NII NACSIS-CAT ID (NCID)
    AA11307372
  • Text Lang
    JPN
  • Article Type
    Journal Article
  • ISSN
    13446460
  • NDL Article ID
    6170700
  • NDL Call No.
    Z74-B503
  • Data Source
    CJP  CJPref  NDL  J-STAGE 
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