The thermal stress analysis of a ceramic gas-turbine stator blade is reported. A three-dimensional analysis, using finite-element computer programs, first calculates the temperature distribution from a sudden up-shock environment applied to the blade through experimentally determined convection boundary conditions. This time-dependent temperature field is then used to calculate the stress state at discrete times for an appropriate boundary-condition constraint. The stress calculations indicate that peak stresses occur at about 4 s and are a result of incompatible bending and displacement between the three main components of the structure. The emphasis is on the general phenomenology of the deformation process through which the stresses are developed.
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