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.
|ジャーナル||Ceramic Engineering and Science Proceedings|
|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 2004 → 30 1月 2004