Abstract
The gas turbine components of jet engines and power plants are usually subjected to cyclic stresses and strains during thermal transients induced by start up and shut down. The resulting thermal/mechanical fatigue cycling determines times to failure and fracture mode of the components that are not always well reproduced by laboratory isothermal low cycle fatigue tests. In order to improve the information on high temperature mechanical properties of the alloys used for turbine components like vanes and blades, the thermal mechanical fatigue technique was introduced several years ago [1, 2]. The most important advantage of this technique is the capability to test the material with temperature and strain conditions as close as possible to those of the components in service, in particular for those new, high technology alloys that may exhibit peculiar response to in service loading, due to heterogeneity, anisotropy, etc. [3].
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