Estimation of Mode Transition in a Supersonic Combustor

• NODA Junji

  Department of Aerospace Engineering, Tohoku University

• MURAKAMI Atsuo

  Japan Aerospace Exploration Agency, Kakuda Space Center

• KUDO Kenji

  Japan Aerospace Exploration Agency, Kakuda Space Center

• TOMIOKA Sadatake

  Japan Aerospace Exploration Agency, Kakuda Space Center

抄録

A quasi-one dimensional calculation was carried out to figure out supersonic combustor performances. Three flow tubes were considered in the combustor region. Those were an air-flow-tube, a combustion-flow-tube and a fuel-flow-tube. A Mach=1 condition was assumed in the combustion-flow-tube. The estimation of a mode-transition was considered as a result of thermal choking. Both clean and vitiated inflows were tested with the calculation model. Experimental combustion tests were also carried out to compare and confirm the validity of calculated results. Mode-transition equivalence ratios and combustor wall pressure distributions were focused to compare between calculated and experimental results. The calculation model estimated the mode-transition equivalence ratio and the thrust performance with the relative errors at about 11% and 6% compared to the experimental results, respectively.

収録刊行物

• Journal of Thermal Science and Technology

  Journal of Thermal Science and Technology 8 (2), 353-362, 2013

  一般社団法人日本機械学会・社団法人日本伝熱学会

キーワード

• Supersonic Combustor
• Flame Holding Model
• Mode Transition
• Thermal Choking
• One-Dimensional Calculation

詳細情報

• CRID: 1390282680222212224
• NII論文ID: 130003366742
• DOI: 10.1299/jtst.8.353
• BIBCODE: 2013JJTST...8..353N
• COI: 1:CAS:528:DC%2BC3sXhsVSntrjI
• ISSN: 18805566
• Web Site: https://www.jstage.jst.go.jp/article/jtst/8/2/8_353/_pdf
• 本文言語コード: en
• データソース種別:
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