Estimation of Mode Transition in a Supersonic Combustor

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概要

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• 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.

著者

• 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

関連論文

• Estimation of Enthalpy Effects in Direct-Connect Dual-Mode Combustor
• 213 Prediction of the Whole Stress-strain Curve and Final Composite Strength of GFRP Cross-ply Laminates
• Estimation of Mode Transition in a Supersonic Combustor

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