CMC combustor liner design for a model ram jet engine

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

Research output: Contribution to journalConference articlepeer-review

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)51-56
Number of pages6
JournalCeramic Engineering and Science Proceedings
Volume25
Issue number3
Publication statusPublished - 1 Dec 2004
Event28th International Conference on Advanced Ceramics and Composites - Cocoa Beach, FL, United States
Duration: 25 Jan 200430 Jan 2004

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