Stresses due to temperature gradients in ceramic-matrix-composite aerospace components

Ceramic-matrix composites (CMCs) are being considered as replacement materi als for divergent flaps and seals in advanced aerospace turbine engines. Du ring ser,ice, these components are subjected to severe temperature gradient s across the width of the flaps. This paper discusses an analytical procedu re to estimate the stresses generated in the CMC naps due to the temperatur e gradients. The analytical procedure can be used for a material with nonli near temperature-dependent stress-strain behavior. This procedure mas used to predict the thermal stresses in four candidate CMC systems due to temper ature gradients. The thermal stresses along the edges typically exceed the proportional limit, and sometimes the fatigue limit of the CMC.