ABSTRACT
Acknowledgments .........................................................................................................................432
References .....................................................................................................................................432
Considerable efforts have been made to develop new high-temperature materials for gas turbine
engine applications. These efforts have been motivated by the desire to increase the thrust to weigh
ratio by increasing the operating temperature of the engine. Since Ni-based superalloys are
currently used at about 0.8-0.9 of the melting point, any increase in the engine operating tempera-
ture requires new structural materials that can withstand the higher temperature requirements [1].
