CMC combustor liner design for a model ram jet engine

Tetsuya Morimoto, Shinji Ogihara, Hideyuki Taguchi, Takayuki Kojima, Kazuo Shimodaira, Keiichi Okai, Hisao Futamura

研究成果: Conference article査読

1 被引用数 (Scopus)

抄録

The development of high temperature resistant ceramic fibers has led to potential applications of ceramic matrix composites (CMCs) for aerospace engine components such as combustion chamber liner, turbine blade, and nozzle. The superior temperature capability of CMCs may then enable in the near future the turbine based combined cycle (TBCC) be the practical thruster for the launch system of two-stages to orbit (TSTO). The current study presents an engineering approach to design the CMC combustion liner for a model RAM jet engine that will be tested in supersonic wind tunnel. FEM thermal analyses have revealed with the thermal parameters of Tyrannohex and SA-Tyrannohex SiC/SiC composites (UBE Industry Co., UBE Japan) the maximum heat flux through the combustor liner implying the limitation in the engine operation.

本文言語English
ページ(範囲)51-56
ページ数6
ジャーナルCeramic Engineering and Science Proceedings
25
3
出版ステータスPublished - 1 12月 2004
イベント28th International Conference on Advanced Ceramics and Composites - Cocoa Beach, FL, United States
継続期間: 25 1月 200430 1月 2004

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