Abstract
The work is a part of a major study to develop design analysis methods for strength and life of CMC structural joints. This paper describes results of thermomechanical fatigue tests conducted on open hole ceramic matrix composite laminated plates. The open hole represent the zero load transfer in a joint. The thermomechanical spectrum loads included mechanical load cycle blocks of various stress levels and stress ratios. The thermal loads were varied simultaneously with mechanical loads for the duration of a representative generic flight. The spectrum peak stress versus life data was developed for the case when the peak temperature is 1500 F. An empirical relation to describe the fatigue life is presented. The results show that a CMC laminate with an open hole spend most of the life during initiation.
