Thermal stress analysis of layered cylindrical shells

The development of a thermal stress analysis capability based on classical shell theory, for the analysis of panels with all four edges free, is described for use in the design of layered metal-ceramic composite panels employed as abradable tip seals in jet engines. The material properties, which may be functions of temperature, can be isotropic, transversely isotropic, or orthotropic, and a one-dimensional heat transfer analysis is permitted by the radial direction of all heat flow. The analysis capability is used to explain fractures and deformations resulting from fabrication and anticipated use, and may be further employed in the development of alternative fabrication strategies to maximize production yields.