Journal
6TH INTERNATIONAL CONFERENCE ON CREEP, FATIGUE AND CREEP-FATIGUE INTERACTION
Volume 55, Issue -, Pages 210-213Publisher
ELSEVIER SCIENCE BV
DOI: 10.1016/j.proeng.2013.03.244
Keywords
Thermal barrier coating; thermo-mechanical fatigue; thermo-gradient mechanical fatigue; failure mechanism; life assessment
Funding
- National Research Foundation of Korea(NRF)
- Ministry of Education, Science and Technology [2012M2A8A1029423]
- National Research Foundation of Korea [2012M2A8A1029423] Funding Source: Korea Institute of Science & Technology Information (KISTI), National Science & Technology Information Service (NTIS)
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A gas turbine blade is under centrifugal force owing to high speed rotation and is under thermal fatigue owing to hot gas during the DSS (Daily Start and Stop) operation. Also. thermal barrier coating (TBC) is applied to protect a blade of gas turbine system from high temperature gas and to lower the surface temperature of the blade. The failure of TBC is directly connected with the failure of the blade because of excessive local degradation at the location of TBC failure. In this study, thermo-gradient mechanical fatigue (TGMF) tests by a furnace which can control heat flux directly have been performed to evaluate the thermal fatigue characteristics between a coated specimen and an uncoated specimen. Also, the failure mechanism of the TBC under TGMF condition has been estimated by micro-structure analysis at the cross-section of fractured specimen. (C) 2013 The Authors. Published by Elsevier Ltd.
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