SiC-based ceramic matrix composite behavior enhancement for gas turbines hot sections

Conference Dates

November 5-9, 2017


Silicon carbide fibers reinforced silicon carbide based-matrix composites (SiC/SiC CMC’s), are probably becoming a major leading alternative for the design and manufacturing of the next gaz turbine engines hot parts as airfoils, shroud, combustion chambers. These materials offer higher temperature capability than the current state-of-the-art metallic superalloys and tougher than the monolithic ceramic. The growing interest in CMC technologies development is directly linked to the new short-term engine design constraints in the context of air travel booming, namely : a drastic decreasing of community noise and air polluting emissions and a specific fuel consumption decrease. During the last fifteen years, substantial research efforts have been devoted towards evaluating for a wide range of CMCs, as oxide and carbide and manufaturing routes, as CVI, MI, powder impregnation, PIP.

Building on past materials efforts in the field of both space launchers and military engines aircraft, Safran continued to enhance CMC technologies for commercial aircraft engines. Considering this new target, one of the key issues related to this emerging technology is to develop and industrialize materials offering high thermomechanical design allowables and stable lifetime properties, in representative environment. To reach these goals, an important work has been done, in the implementation of Melt –Infiltrated SiC/SiC CMC and T/EBC top-coat.

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