Abstract
Since gas turbines operate under extremely high temperatures, the hot-section parts of gas turbines should be protected from severe environmental conditions. Thermal Barrier Coating (TBC) is a protection technique that lowers the surface temperature of the hot-section parts. To design reliable gas turbines, the delamination life of TBC should be accurately evaluated. This study evaluated the delamination life of TBC by conducting a burner-rig test simulation of thermal fatigue conditions using a hot flame. Two types of TBCs were considered: one with vertical cracks and the other without vertical cracks. To evaluate the effects of pre-isothermal deterioration on thermal fatigue life under flame conditions, burner-rig tests were performed using isothermally deteriorated specimens. The burner-rig tests were conducted until the coating layer was completely delaminated. Using the tests results, predictive equations for delamination life and delaminated TBC area were derived and analyzed.
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Abbreviations
- N:
-
Number of cycle of burner-rig test
- A:
-
Percentage of delaminated area of coating specimen
- T:
-
Deterioration time at 1100°C
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Yun, J., Kim, Y., Lee, JM. et al. The study on delamination life of TBC through burner-rig test. Int. J. Precis. Eng. Manuf. 18, 555–560 (2017). https://doi.org/10.1007/s12541-017-0066-8
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DOI: https://doi.org/10.1007/s12541-017-0066-8