Hot flowpath components in aircraft gas turbine engines are subject to a severe operating environment. The large thermal gradients can produce high thermal strains that, when combined with mechanical loads and a deleterious environment, can lead to premature failure. To combat this possibility, designers spend considerable time determining the stress and strain fields in these components as the parts undergo typical operating histories. These field quantities can then be used to determine failure parameters and determine life limiting locations. The field determinations can be difficult and, in combination with numerous potential failure mechanisms, the structural assurance process can take a considerable time to complete. To shorten this process, a personal computer (PC) based preliminary design system has been developed. This system, called Thermo-mechanical Fatigue—Structural Life Assessment Method (TMFSLAM), permits the user to rapidly evaluate the interactive effects of duty cycle, geometry, and materials on component life. The quantitative results determined by TMFSLAM will be available to make decisions on design changes, material substitution, etc.

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