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| Failure Analysis of Thermal Barrier Coating Being Subjected to Lateral Thermal Gradient on Surface |
| CHEN Chen1,2, GUO Hongbo2, GONG Shengkai2 |
1. AVIC Commercial Aircraft Engine Co. Ltd., Shanghai 200241, China;
2. School of Material Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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Abstract Due to the combustion chamber usually provide flam with a non-uniform temperature field, therefore, a lateral temperature gradient should exist on the surface of nozzle guide-vanes for a gas turbine. In the present article, the structure evolution of thermal barrier coatings on nozzle guide-vanes was examined under the action of the above mentioned lateral temperature gradient by means of a home madeinfrared thermal shock testing system combined with impedance spectroscopy measurement. Meanwhile, the failure analysis of thermal barrier coatings being subjected to thermo-mechanical loading was also studied using finite element analysis. It's found that with constrain at both ends of a tube, cracks are apt to initiate at the edge of a heated area.
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